AST Requirements Specificationemits.sso.esa.int/emits-doc/ASTRIUMLIM/LISA_AST/S2... · The AST for Lisa Pathfinder will be used during certain mission phases, covering the LEOP, the

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CONTENTS

1. INTRODUCTION AND SCOPE.....................................................................................................................5 1.1 Introduction.............................................................................................................................................5 1.2 Scope .....................................................................................................................................................7 1.3 Summary Description .............................................................................................................................7 1.4 Definition of Performance Phases..........................................................................................................8

2. DOCUMENTS................................................................................................................................................9 2.1 Applicable Documents............................................................................................................................9 2.2 Applicable Standards .............................................................................................................................9 2.3 Reference Documents..........................................................................................................................10

3. FUNCTIONAL AND PERFORMANCE REQUIREMENTS..........................................................................11 3.1 Reference frames definition .................................................................................................................11

3.1.1 AST Mechanical reference frame (MRF) definition....................................................................11 3.1.2 AST Alignment reference frame (ARF) definition.......................................................................11 3.1.3 AST Measurement reference frame (MeasRF) definition ..........................................................11 3.1.4 AST Inertial Reference Frame (IRF) Definition ..........................................................................11 3.1.5 Quaternion Format .....................................................................................................................12

3.2 AST operating modes...........................................................................................................................12 3.3 Input Data .............................................................................................................................................13 3.4 Output data...........................................................................................................................................14 3.5 Conditions for performance requirements............................................................................................16

3.5.1 General.......................................................................................................................................16 3.5.2 Dynamics conditions ..................................................................................................................16 3.5.3 Optical environment ...................................................................................................................17 3.5.4 Lifetime.......................................................................................................................................17 3.5.5 Environment ...............................................................................................................................17

3.6 Performance Requirements .................................................................................................................18 3.6.1 Measurement Acquisition and Availability..................................................................................18 3.6.2 Measurement Performance........................................................................................................19

3.7 FDIR .....................................................................................................................................................21

4. UNIT SPECIFIC DESIGN AND INTERFACE REQUIREMENTS ...............................................................22 4.1 Implementation Requirements .............................................................................................................22 4.2 Mechanical Design and Interface Requirements .................................................................................22

4.2.1 Mass...........................................................................................................................................22 4.2.2 Centre of Gravity ........................................................................................................................22 4.2.3 Envelope ....................................................................................................................................22 4.2.4 Unit Attachment..........................................................................................................................23

4.3 Thermal Design and Interface ..............................................................................................................25 4.4 Electrical Design and Interface.............................................................................................................27

4.4.1 Power Consumption ...................................................................................................................27 4.4.2 Power Interface ..........................................................................................................................28 4.4.3 Harness ......................................................................................................................................28 4.4.4 Interface to Satellite Data Handling............................................................................................28 4.4.5 Test Equipment ..........................................................................................................................29

5. GENERAL DESIGN AND INTERFACE REQUIREMENTS ........................................................................32 5.1 General .................................................................................................................................................32 5.2 Mechanical ...........................................................................................................................................32 5.3 Thermal ................................................................................................................................................32

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5.4 Electrical ...............................................................................................................................................32 5.5 Identification & Marking ........................................................................................................................34

6. VERIFICATION REQUIREMENTS .............................................................................................................35

7. PRODUCT ASSURANCE REQUIREMENTS .............................................................................................36

8. ACRONYMS................................................................................................................................................37

9. GDIR APPLICABILITY MATRIX..................................................................................................................38

TABLES Table 4.3-1: AST Thermal Environment Non Science Phase Performance ...................................................25 Table 4.3-2: AST Thermal Environment for Science Phase Performance Requirements ..............................26 Table 5.4-1: Magnetic Fields ...........................................................................................................................33

FIGURES Figure 1.1-1: The LISA mission will use an ultra-precise interferometry through three satellites flying in

formation on an Earth-like orbit to measure ripples in space-time ............................................................6 Figure 1.3-1: Expected AST Mounting on the Spacecraft .................................................................................7 Figure 3.2-1: AST Modes ................................................................................................................................13 Figure 4.2-1: AST Bracket Envelope...............................................................................................................24 Figure 4.3-1: Spacecraft External Geometry For Thermal Analysis................................................................27

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1. INTRODUCTION AND SCOPE

1.1 Introduction LISA is a co-operative program between ESA and NASA to detect and measure `ripples' in the fabric of space-time to verify tenets of fundamental physics. The program includes two space missions; The LISA PATHFINDER mission and the LISA mission itself. LISA will consist of three spacecraft flying in a quasi-equilateral triangular formation, in a trailing Earth orbit at some 20 deg behind the Earth. Within each spacecraft, a measurement system consisting of two test masses, associated laser interferometer measurement systems, and electronics will detect and measure low frequency gravitational waves. The test masses are maintained in a drag-free environment, i.e. shielded from spurious external forces, by using low thrust propulsion. This mission is currently in its formulation stage. LISA PATHFINDER is a precursor mission to LISA that aims to verify most of the challenging technologies necessary for LISA.

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Figure 1.1-1: The LISA mission will use an ultra-precise interferometry through three satellites flying

in formation on an Earth-like orbit to measure ripples in space-time

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1.2 Scope This document defines the mission, performances, environment, interface and design requirements for the Autonomous Star Tracker (AST) for the Lisa Pathfinder Attitude and Orbit Control Subsystem (AOCS). Each requirement is identified by a unique requirement number and is written in italics. Each requirement is proceeded by a summary line that contains the following fields, delimited by "/". � <Doors Requirement Number> TKS-xyz. This is a unique number, assigned consecutively � <Created From> Shows parent requirement � <Test Method> T= Test, A = Analysis, I = Inspection, R = Review of Design Text that is not written in italics is there for information purposes only (e.g. background information that clarifies the origins of the requirement): it does not constitute part of the requirement itself.

1.3 Summary Description The AST for Lisa Pathfinder will be used during certain mission phases, covering the LEOP, the transfer, and mission operations in the Lagrange 1 (L1) orbit. When used, the AST will be used as the primary attitude measurement used either alone or as part of a Kalman filter combining AST measurements with rate measurements from a gyro package. It is intended to procure 2 separate devices with one primarily acting as the cold redundant back up for the other. There are some exceptions to this where both units may be used simultaneously, one for nominal control and the other for failure detection. The nominal configuration is to have both units co-aligned with their boresights pointed in the spacecraft XY plane. However the exact angle in this plane is not yet fully fixed. This is shown in Figure 1.3-1.

AST-1

AST-2

Figure 1.3-1: Expected AST Mounting on the Spacecraft

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1.4 Definition of Performance Phases In terms of AST measurement performance requirements there are two distinct phases: Science Phase and Non-Science Phase. The measurement performance requirements for the Science phase of the mission are expressed as a function of frequency in terms of a PSD. This is critical for the science phase mission performance. These requirements are presented in Section 3.6.2.1 Science Phase Measurement Performance Requirements. Furthermore, during this phase the spacecraft dynamics and thermal conditions are different and generally more benign than during other mission phases and so specific requirements apply in this regard. The dynamics and thermal requirements applicable during this phase are presented in Section 3.5.2.3 Science Phase Dynamics Range and in requirement AST-1489, respectively. This ensures both that the relevant conditions are applied when assessing compliance and that the supplier need not adhere to overly stringent requirements unnecessarily. Measurement performance requirements are also placed for non-Science phases of the mission and are presented in Section 3.6.2.2 Non-Science Measurement Performance Requirements. These requirements must be met under the general conditions for performance presented throughout the specification and in particular in Section 3.5 and Section 4.3. It is also anticipated that during non-science phase two levels of performance may be provided by the AST depending on the rate and acceleration of the spacecraft. Two ranges of dynamics conditions are described in Section 3.5.2.1 and Section 3.5.2.2. The non-science measurement performance must be provided for the Nominal Dynamics Range. During the Degraded Dynamics Range the unit must be able to acquire and maintain tracking but no specific accuracy requirements are placed. The supplier must nevertheless state the accuracy achieved for this range of dynamics. For the degraded dynamics range an increase in the time to acquire tracking is also permitted. The acquisition and tracking time requirements are given in Section 3.6.1.1 and Section 3.6.1.2.

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2. DOCUMENTS The following documents, at the latest issue unless otherwise stated, are relevant documents to this specification. In case of conflict between any of these documents and the contents of this specification, the requirements of this specification shall take precedence. Any such conflict shall be reported to Astrium.

2.1 Applicable Documents The following documents form a part of this specification to the extent specified.

AD-14 S2.ASU.RS.1005 PA Requirements for Subcontractors

AD-15 S2.SYS.RS.1001 Software PA Requirements for Subcontractors

AD-17 S2.ASU.RS.2031 LISA Pathfinder GDIR

AD-19 S2.ASU.RS.2039 LISA Pathfinder MIL-1553-B Data Bus Utilization Specification

AD-20 S2.SYS.ICD.2001 LISA Pathfinder Packet Utilization Standard

AD-21 S2.ASU.LI.1006 Acronyms and Abbreviations

AD-22 S2.ASU.RS.5038 EGSE Overall Requirements Specification

2.2 Applicable Standards The following Engineering Documents and Standards form part of this specification to the extent specified.

STD-1 Space Engineering - Space Environment, ECSS-E-10-04A, 21.01.2000

STD-2 Space Engineering - Electrical and Electronic, ECSS-E-20A, 04.10.99

STD-3 Space Engineering - Mechanical, ECSS-E-30 Part 1A to 8A, 25.04.2000

STD-4 ESA Error Handbook, EHB.DGD.REP.002, Iss. 1, 19.02.1993

STD-6 Packet Telemetry Standard, PSS-04-106, Issue 1, January 1988

STD-7 Telemetry Channel Coding Standard, PSS-04-103 Issue 1, September 1989

STD-8 Packet Utilization Standard, ECSS-E-70-41A, 30.01.2003

STD-9 Packet Telecommand Standard, PSS-04-107, Issue 2, April 1992

STD-12 Space Engineering - Software, ECSS-E-40B, November 2003

STD-16 Space Engineering - Verification, ECSS-E-10-02A, 17.11.1998

STD-17 Space Engineering - Testing, ECSS-E-10-03A, 15.02.2002

STD-19 Structural Materials Handbook, PSS-03-203, Volumes 1 & 2

STD-27 MIL-STD-1553B 21 September 1978 + Notice 2 8 September 1986, Notice 3 31 January 1993, Notice 4 15 January 1996.

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2.3 Reference Documents The following documents do not form part of this specification but were used during its preparation.

None

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3. FUNCTIONAL AND PERFORMANCE REQUIREMENTS

3.1 Reference frames definition

3.1.1 AST Mechanical reference frame (MRF) definition AST-36/CREATED/I,R

The AST (optical head and electronics) shall employ a right handed Cartesian reference frame with its origin at the reference point of the AST, and the orientation of the axes as defined below. The Z_ast_mF axis is aligned with the AST line of sight and oriented from the platform to space. The X_ast_mF axis shall be in the mounting plate plane and shall be clearly identified on the AST hardware. The Y_ast_mF axis is defined in order to have a right-hand orthogonal reference frame. The definition of this reference frame shall be defined in the AST Mechanical Interface Control Document. Note: Should the AST have a modular architecture (Optical unit + Electronic unit), this requirement is applicable to the optical unit.

3.1.2 AST Alignment reference frame (ARF) definition AST-38/CREATED/I,R

The AST optical head shall include an optical reference cube for the purpose of aligning the AST optical head onto the spacecraft.

AST-327/CREATED/R The normals to three of the optical cube faces shall be used to form a right handed Cartesian reference frame, the Alignment Reference Frame (O_ast_aF, X_ast_aF, Y_ast_aF, Z_ast_aF) as shown in the figure cited in requirement GDI-188 of AD-17.

3.1.3 AST Measurement reference frame (MeasRF) definition AST-328/CREATED/R

The AST shall employ a right handed Cartesian reference frame that has one of its axes perpendicular to the detector (e.g. CCD, APS) and pointing away from the detector towards Space and the other 2 axes (nominally) in the plane of the detector and normal to the first axis. This shall be designated the AST Measurement Reference Frame.

AST-41/CREATED/R The AST supplier shall deliver the 3x3-transfer matrix from the AST Alignment reference frame to the AST Measurement reference frame.

AST-316/CREATED/T,A,R The delivered transfer matrix referred cited in the requirement above shall be measured before and after all the environment tests performed during the acceptance phase.

3.1.4 AST Inertial Reference Frame (IRF) Definition AST-40/CREATED/T,R

The AST shall deliver attitude quaternions defined as the orientation of the AST Measurement reference frame in the Earth Centred Inertial J2000 (true of date) reference frame: · The positive X axis is in the direction of the first point of Aries on 01/01/2000 at 12 noon; · The Z axis is in the direction of the Earth’s North Pole on 01/01/2000 at 12 noon; · The Y axis is constructed such that it is orthogonal to both the X and Z axes, thereby completing right handed reference frame.

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3.1.5 Quaternion Format AST-402/CREATED/T,R

The supplier shall unambiguously define the format and sense of rotation of the output quaternion of the unit.

3.2 AST operating modes The AST modes to be used in flight are shown in Figure 3.2-1 and detailed below. The mode names are for information and clarity with regard to the requirements below.

AST-44/CREATED/T,R The AST shall be able to operate in a Standby mode such that only health data is delivered in the telemetry packet.

AST-330/CREATED/T,R The Standby mode shall always be entered upon the AST being powered ON.

AST-45/CREATED/T,R The AST shall be able to operate in an Acquisition & Tracking mode such that it automatically acquires the 3-axis attitude from “lost in space” conditions, and thereafter delivers updated quaternions at the required frequency.

AST-51/CREATED/T The AST shall be available in Standby mode and ready to enter Acquisition & Tracking mode or Aided Acquisition & Tracking mode less than 600 sec after being powered.

AST-46/CREATED/T,R The AST shall be able to operate in an Aided Acquisition & Tracking mode such that the AST receives a predicted quaternion and rate (as defined in AST-54) which it then uses to acquire the 3 axis attitude, and thereafter deliver the updated quaternions as in the Acquisition & Tracking mode.

Note that the purpose of this ‘Aided tracking’ mode is to allow the star tracker to determine the three axis attitude, after a temporary outage, significantly more quickly than it would do from a ‘lost in space’ situation.

AST-47/CREATED/T,R The AST shall be able to operate an IMAGE mode such that parts of the (or the full) detector image, prior to any correction being applied on the video, is made available, upon request, via one or more telemetry packets.

AST-1549/CREATED/A,R The supplier shall define the maximum available portion of the detector image which can be downloaded.

Note that requirement above does not require the detector image to be taken, stored and transmitted in one operation. If need be this can be done in stages and spread over several telemetry packets.

AST-333/CREATED/T,R It shall be possible to define, via command, the portion of the detector, cited in the Image Mode requirement above, by specifying it in terms of the range of abscissa and ordinates of the pixels contained within it (i.e. a window) where the range can extend from one pixel to the maximum available portion of the detector.

AST-48/CREATED/T,R The AST shall be able to operate in a DOWNLOAD/UPLOAD modes such that it is possible to: � Download all of the AST software and data/parameter settings. � Modify any part of the AST software code and data, including the on-board star catalogue. � Reset the AST software and data RAMS

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�� Modify AST parameter settings by simple telecommands (i.e. not reliant on memory address patching)

The AST mode diagram is shown below:

Stand by mode

Image mode Download/Upload

Mode

Acquisition & trackingMode

Aided Acquisition & Tracking mode

Figure 3.2-1: AST Modes

AST-646/CREATED/R It shall be possible to transition between Standby mode and any other mode cited in Figure 3.2-1 by application of a single telecommand.

AST-1469/CREATED/R It shall be possible to configure the unit to perform an autonomous transition (without need for TC) between Standby mode and Acquisition & Tracking or Aided Acquisition & Tracking mode.

3.3 Input Data AST-54/CREATED/T,R

When operating in the Aided Acquisition & Tracking Mode the AST shall accept: � a quaternion representing the three-axis attitude of the AST Measurement Reference Frame in the J2000 inertial frame and � the spacecraft body rates expressed in the AST Measurement Reference Frame.

AST-56/CREATED/T,R The AST shall be able to apply corrections for all relativistic effects due to the motion of the Earth.

AST-334/CREATED/T,R In order to meet the requirement AST-56, the AST shall accept and use the Julian date, sent via the data interface with the spacecraft computer.

The time accuracy of the Julian date provided to the AST will be in the order of 1 second.

AST-335/CREATED/T,R It shall be possible to enable/disable the internal correction function for relativistic effects cited in AST-56 via telecommand.

AST-648/CREATED/T,A,R The AST shall continue to operate even when no relativistic corrections have been applied.

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AST-649/CREATED/R The supplier shall quantify the degradation in performance if relativistic effects are not applied.

AST-1470/CREATED/R No in-orbit calibrations shall be necessary in order to satisfy the performance requirements cited in Section 3.6.

AST-1569/CREATED/R In case of partial or non-compliance with AST-1470, the following requirements AST-1570, AST-57 and AST-337 shall apply.

AST-1570/CREATED/R For any required in-orbit calibrations, full details, including a procedure, shall be provided and the number and duration shall be minimised.

AST-57/CREATED/T,R The supplier shall identify all parameters that may need to be recalibrated in-flight.

AST-337/CREATED/T,A,R The supplier shall quantify the effect of each the calibrations cited in AST-57 above upon the quaternion output by the AST.

AST-1416/CREATED/T,A,R For Aided Acquisition & Tracking mode, the accuracy of the attitude quaternion and rates provided to the AST in order to meet the acquisition time requirements cited in AST-451 and AST-454 shall be defined by the supplier.

3.4 Output data AST-59/CREATED/R

The AST shall provide a cyclic telemetry output at a frequency of at least 2Hz.

AST-60/CREATED/T,R In all modes, the AST shall always provide the following basic telemetry packet as part of its cyclic telemetry output: � The AST current mode identification � The AST health data including at least critical AST temperatures information.

AST-1411/CREATED/R In addition to identification of the modes defined in section 3.2 the current mode identification shall indicate if the unit is in the Acquisition or Tracking phase of the Acquisition & Tracking or Aided Acquisition & Tracking mode.

AST-61/CREATED/T,R Whilst operating in either Acquisition & Tracking Mode or Aided Acquisition & Tracking Mode the AST shall, in addition to the basic telemetry packet cited in the requirement above (AST-60), provide the following as part of its telemetry output: � the attitude measurement packet as defined below, � upon command, the raw data telemetry packet as defined in AST-63.

AST-62/CREATED/T,R The attitude measurement packet shall contain: � The quaternion representing the three axis attitude of the AST Measurement Reference Frame with respect to the inertial J2000 reference frame. � A Validity Flag indicating whether or not a valid attitude quaternion is available in the delivered

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telemetry. � Quality Index of the measurement. � A datation of the measurement (defined as the middle of the integration period) with respect to the latest time reference signal provided by the platform, as defined in AST-66.

AST-552/CREATED/T,A The Validity Flag cited in AST-62 shall provide the validity status of the AST measurement. The Validity Flag shall be set when the accuracy of the measurement is better than 1 degree (3 sigma) (TBC) for each axis in the AST Measurement Reference Frame.

AST-1471/CREATED/T,A The reliability of the Validity Flag shall be at least 99.99% i.e. the validity status flag must correctly identify the validity of the measurement for 99.99% of the measurements produced by the unit.

AST-553/CREATED/T,A The probability of a false positive reading in the Validity Flag cited in AST-62 and AST-552 shall be less than 0.01%.

A false positive is defined as when the Validity Flag indicates a valid signal when the AST quaternion has not met the criterion defined in AST-552 for being valid.

AST-644/CREATED/A,R When the AST boresight is within an Earth, Moon or Sun exclusion region cited in AST-74 the Validity Flag shall indicate an invalid measurement.

AST-1474/CREATED/R The full functionality and behaviour of the Quality Index shall be provided by the supplier in the first instance at the time of the proposal.

AST-63/CREATED/T,R Irrespective of whether or not a valid three axis attitude is available, the raw data telemetry packet shall, for each measured star, contain: � Direction of the measured star in the AST Measurement Reference Frame. � Brightness (i.e. magnitude) of the measured star. � Star index � A status word detailing the type of corrections (aberration, precession etc.) applied on the star measurement.

AST-64/CREATED/T,R The accuracy of the star measurements in the raw data telemetry packet shall be at least the same as that used in the computation of the three axis attitude.

AST-340/CREATED/R If the star measurements are being internally compensated for errors (e.g. relativistic errors, proper motion, biases, focal length etc.) before being used in the three axis attitude computation, then the compensated values of the star measurements shall be the ones reported in the raw telemetry packet i.e. the star measurements actually used to determine the three axis attitude.

AST-65/CREATED/T,R The maximum delay between the middle of integration period and the availability of the corresponding telemetry packet at the AST interface shall be less than 750ms

AST-66/CREATED/T,R The AST shall receive an external 2 Pulse per Second (PPS) time reference signal synchronisation pulse from the satellite through a dedicated interface as defined in AD-17.

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AST-67/CREATED/T,R In the event that that the AST does not receive a synchronisation pulse then the AST shall raise a flag that will be made available as part of its output TM packet. This flag shall be reset upon the receipt of the external synchronisation pulse.

AST-68/CREATED/T The accuracy of the measurement datation (middle of integration period) with respect to the latest time reference signal shall be better than 1ms.

3.5 Conditions for performance requirements

3.5.1 General AST-548/CREATED/T,A,R

The performance requirements (cited in Section 3.6) shall be met under worst case BOL and EOL conditions in the presence of all known effects influencing this performance to include (where appropriate) but not restricted to environmental, launch loads, spacecraft dynamic conditions, ageing, radiation environment, sensor bias, sensor noise, quantisation, temperature effects, unit conversion factor errors, 1g to 0g effects and SEU's.

3.5.2 Dynamics conditions

3.5.2.1 Nominal Dynamics Range AST-403/CREATED [RD-93]/T,A

The AST shall acquire and maintain tracking and offer measurement accuracy as cited in Section 3.6.2.2 with rates of up to 0.2 deg/s around any axis in the AST Measurement Reference Frame.

AST-405/CREATED [RD-93]/T,A The AST shall acquire and maintain tracking and offer measurement accuracy as cited in Section 3.6.2.2 with accelerations of up to 0.1 deg/s2 around any axis in the AST Measurement Reference Frame.

The range of angular rates and accelerations cited in AST-403 and AST-405 under which performance levels cited in Section 3.6.2.2 shall be provided is designated Nominal Dynamics Range.

3.5.2.2 Degraded Dynamics Range AST-404/CREATED [RD-93]/T,A

The AST shall acquire and maintain tracking but is permitted to offer degraded performance with rates >0.2 deg/s and <1.0deg/s around any axis in the AST measurement reference frame.

AST-406/CREATED [RD-93]/T,A The AST shall acquire and maintain tracking but is permitted to offer degraded performance with accelerations >0.1 deg/s2 and <0.5deg/s2 around any axis in the AST measurement reference frame.

The range of angular rates and accelerations cited in AST-404 and AST-406 under which degraded performance can be provided is designated Degraded Dynamics Range.

3.5.2.3 Science Phase Dynamics Range AST-1486/CREATED/T,A

During the science phases of the mission the range of spacecraft dynamics is different compared with the range expected for other phases of the mission. The measurement performance requirements cited in Section 3.6.2.1 shall be met under the following dynamics range cited in requirements AST-1487 and AST-1488.

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AST-1487/CREATED/T,A The AST shall offer the performance cited in Section 3.6.2.1 with angular rates in the range 0 to 5e-3 deg/s around any axis in the AST Measurement Reference Frame.

AST-1488/CREATED/T,A The AST shall offer the performance cited in Section 3.6.2.1 with angular acceleration in the range 0 to 1e-4 deg/s2 around any axis in the AST Measurement Reference Frame.

The above dynamic conditions are provided to allow the supplier to assess the performance in the presence of the rates and accelerations present during the science phase of the mission. The above conditions do not explicitly define a dynamic profile since this varies with the specific science AOCS mode. The supplier is expected to determine the motion profile (within the above envelope) which results in the worst case performance.

3.5.3 Optical environment AST-74/CREATED/A

The performance levels cited in Section 3.6 shall be guaranteed in the following domain: a) The angle between the AST line of sight and the Sun direction is higher than 45°. b) The angle between the AST line of sight and the Earth limb (at ground level) is higher than 30°. c) The angle between the AST line of sight and the Moon direction is higher than 20° (from centre of Moon). d) The angle between the AST line of sight and direction of any spacecraft element (straylight source) is greater than 45 degrees.

Note The minimum distance between spacecraft and centre of moon is approximately 100,000 km.

AST-76/CREATED/T,R Any degradation of the output performance, beyond the required levels, due to the measured optical environment, shall be detected and flagged in the cyclic telemetry output packets Validity flag and/or Quality Index.

AST-77/CREATED/T,A The AST shall offer the performance levels cited in Section 3.6 in the presence of up to 3 (TBC) false stars in the FOV, with following characteristics: � Magnitude between -1 and +5, � Size similar to the one of stars or planets, � Apparent motion rate differs at least by 0.02°/s from stars motion rate.

False Stars are defined as non stellar objects appearing on the detector which are indistinguishable from stars such as planets, spacecraft, debris etc.

3.5.4 Lifetime AST-550/CREATED [RD-20]/T,A

The unit shall comply with the lifetime requirements cited in AD-17.

3.5.5 Environment AST-551/CREATED/T,A

The unit shall offer the performance levels cited in Section 3.6 under the environmental conditions cited in AD-17.

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3.6 Performance Requirements

3.6.1 Measurement Acquisition and Availability

3.6.1.1 Lost in Space Acquisition Time Lost in Space is defined as when the AST has no a priori knowledge whatsoever of the attitude.

AST-1480/CREATED/A,R The Lost in Space Acquisition Time requirements shall be met in the presence of all conditions cited in Section 3.5 as well as in the presence of all Thermal, Mechanical and Environmental requirements stated in or made applicable to this specification, unless otherwise stated.

AST-445/CREATED/T,A Under the 'lost in space' scenario, while in the Nominal Dynamics Range and not within an exclusion region (as cited in AST-74), the time taken for the AST to deliver a valid quaternion that represents the three axis attitude at full accuracy shall be less than thirty seconds from the instant that the AST enters the Acquisition & Tracking Mode.

AST-448/CREATED/T,A Under the 'lost in space' scenario, while in the Degraded Dynamics Range and not within an exclusion region (as cited in AST-74), the time taken for the AST to deliver the quaternion that represents the three axis attitude shall be less than sixty seconds from the instant that the AST enters the Acquisition & Tracking Mode.

3.6.1.2 Aided Acquisition Time AST-1481/CREATED/R

The Aided Acquisition Time requirements shall be met in the presence of all conditions cited in Section 3.5 as well as in the presence of all Thermal, Mechanical, Environmental and any other requirements stated in or made applicable to this specification, unless otherwise stated.

AST-451/CREATED/T,A When in Nominal Dynamics Range and not within an exclusion region (as cited in AST-74), the time taken for the AST to deliver a valid quaternion that represents the three axis attitude at full accuracy shall be less than one second from the instant that the AST enters the Aided Acquisition & Tracking Mode.

AST-454/CREATED/T,A When in Degraded Dynamics Range and not within an exclusion region (as cited in AST-74), the time taken for the AST to deliver a valid quaternion that represents the three axis attitude shall be less than three seconds from the instant that the AST enters the Aided Acquisition & Tracking Mode.

3.6.1.3 Availability AST-1482/CREATED/A,R

The Availability requirements shall be met in the presence of all conditions cited in Section 3.5 as well as in the presence of all Thermal, Mechanical, Environmental and any other requirements stated in or made applicable to this specification, unless otherwise stated.

AST-444/CREATED/T,A Apart from the instances when the AST line of sight is within an exclusion region (as cited in AST-74), the AST shall be able to determine the three axis attitude for any AST boresight pointing direction in the celestial sphere (i.e. even in those cases when the star tracker's FOV is directed toward a portion of the celestial sphere in which the sparsity of stars is at its worst).

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AST-455/CREATED/T,A When in Nominal Dynamics Range and not within an exclusion region (as cited in AST-74), and over any 100 second period, more than 99% of the delivered quaternions shall be given at the performance levels cited in Section 3.6.2.2.

AST-1548/CREATED/T,A When in Science Phase Dynamics Range (as cited in section AST1485) and not within an exclusion region (as cited in AST-74), and over any 100 second period, more than 99% of the delivered quaternions shall be given at the performance levels cited in Section 3.6.2.1.

AST-458/CREATED/T,A When in Degraded Dynamics Range, and not within an exclusion region (as cited in AST-74), over any period of 100 seconds, more than 90% of the delivered quaternions shall be provided at TBD accuracy. The supplier shall advise as to the accuracy that is achievable when operating under these conditions.

AST-563/CREATED/T,A The supplier shall advise on the level of performance of the unit with respect to the requirements cited in Section 3.6.2, when the Line of sight of the AST is less than 20 deg from the centre of the Moon.

3.6.2 Measurement Performance In this section the measurement performance requirements are defined. These are firstly defined in terms of frequency dependent performance requirements required for the science phase of the mission. Secondly the rms measurement performance requirements are specified. These shall be met across all mission phases apart from the Science phase.

AST-1483/CREATED/R The Measurement Performance requirements shall be met in the presence of all conditions cited in Section 3.5 as well as in the presence of all Thermal, Mechanical, Environmental and any other requirements stated in or made applicable to this specification, unless otherwise stated.

AST-561/CREATED/T,A Any change in conditions (dynamic conditions, thermal conditions etc) deemed necessary by the supplier in order to meet any requirement defined herein shall be described in detail at the time of the proposal to allow the feasibility of any such modifications to be fully assessed.

AST-1417/CREATED/T,A,R The performance requirements defined herein shall be met in the presence of all error sources.

AST-1484/CREATED/R The supplier shall provide a detailed error budget for the measurement performance for each axis in the AST Measurement Reference Frame of the unit which shall include all relevant contributory error sources.

AST-1551/CREATED/R The detailed error budget cited in AST-1484 shall be subject to agreement and approval by prime.

An example set of potential error classes is presented below: �� Bias errors �� Long term bias stability errors �� Low frequency errors �� Short term thermo-elastic stability errors �� Field of view (low frequency) errors �� Noise Equivalent Angle

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It is expected that the error budget provided should be at this level of detail with the error level provided as well as the frequency range over which it acts.

All values, where applicable, are specified to a confidence level of 68% unless stated otherwise.

AST-432/CREATED/R All measurement requirements shall apply to all 3 axes of the AST Measurement Reference Frame including the boresight axis unless otherwise stated.

The requirements defined in Section 3.6.2.1 and Section 3.6.2.2 should be defined as the measurement performance of the AST sensitive axes of the AST Measurement Reference Frame with respect to the AST Inertial Reference Frame as defined in Section 3.1.3 and Section 3.1.4, respectively.

3.6.2.1 Science Phase Measurement Performance Requirements AST-427/CREATED/R

All PSD figures shall be calculated as a single sided power spectral density and expressed as the square-root PSD with units of arcseconds/sqrt(Hz).

AST-436/CREATED/T,A,R If the requirements in this section are verified using a time history of AST measurements, the AST measurements used to generate the PSD shall be of sufficient duration to ensure that all noise components in the frequency range between 1 mHz and 30 mHz are represented.

If the PSD is generated from a time history of AST measurements, normally the time history should be an order of magnitude longer in duration than the lowest frequency components of interest. The lowest frequency in the above requirements are 1 mHz meaning that the time series should be at least 10000 seconds in duration.

AST-429/CREATED [RD-99]/T,A The AST overall measurement noise spectrum (expressed as a PSD) shall not exceed 32"/rt-Hz in the frequency range from 1mHz up to and including 30 mHz for any AST Measurement Reference Frame axis.

AST-438/CREATED [RD-20, RD-37]/T,A,R The PSD requirement described in AST-429 shall be met for the Science Phase Dynamics Range presented in Section 3.5.2.3.

ASU is aware that low frequency AST noise effects are a function of features such as rate of star motion on the detector. It is therefore considered important to understand how variations in attitude profile can influence AST performance, particularly in the sensitive measurement bandwidth of 1 mHz to 30 mHz.

AST-627/CREATED /R

The PSD requirement described in AST-429 shall be met under the temperature characteristics cited in requirement AST-1489.

The temperature characteristics cited in AST-1489 can be assumed for analysis of the performance requirements in Section 3.6.2.1. This is designed so as to impose the relevant thermal requirements during the Science phase of the mission where the thermal characteristics are different (e.g. narrower range of temperature) than for the other mission phases. It is particularly important to define representative thermal characteristics for this phase due to the link between temperature variation and the frequency dependent noise requirements. All other requirements (RMS etc) shall assume the thermal characteristics defined generally in Section 4.3 and Table AST-409 in particular.

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3.6.2.2 Non-Science Phase Measurement Performance Requirements AST-430/CREATED/T,A

The RMS noise shall not exceed 35" for all error contributions operating in the frequency range (f): 1 mHz <= f <= 1 Hz (or up to sensor bandwidth provided, if higher) for all 3 axes in the AST Measurement Reference Frame.

AST-1490/CREATED/T,A The Bias shall not exceed 30" where the Bias is defined as to include all error contributions operating in the frequency range (f): DC <= f < 1 mHz. for all 3 axes in the AST Measurement Reference Frame.

AST-440/CREATED/T,A Requirements AST-430 and AST-1490 shall be met for the Nominal Dynamics Range presented in Section 3.5.2.1.

AST-1574/CREATED/T,A The supplier shall state the RMS noise and Bias performance levels (as defined in AST-430 and AST-1490) for the Degraded Dynamics Range defined in Section 3.5.2.2.

AST-1492/CREATED/T,A Requirements AST-430, AST-1490 and AST-1574 shall be met under the temperature characteristics cited in requirement AST-409.

3.7 FDIR AST-638/CREATED/T,A

There shall be no failure propagation between units.

AST-639/CREATED/T,A If multiple OH's are connected to a single EU, there shall be no possible failures in the EU which can lead to failure of more than one AST.

AST-640/CREATED/T,A If multiple OH's are connected to a single EU, there shall be no possible failures in a OH which can lead to failure of more than one AST.

AST-1550/CREATED/T,A The AST shall provide upon request all the specific data needed to perform troubleshooting of anomalies, to independently asses whether the unit is providing the correct attitude according to specification or there are problems, in any part of the elaborate chain occurring from detector health to quaternion output.

AST-1410/CREATED/R The precise failure coverage and reliability of the health status telemetry shall be fully described.

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4. UNIT SPECIFIC DESIGN AND INTERFACE REQUIREMENTS

4.1 Implementation Requirements Two ASTs will be mounted on the Lisa Pathfinder spacecraft, and will be co-aligned. They will be operated in both cold redundancy and fully operated simultaneously, depending on the mission phase.

AST-166/CREATED/R The AST shall be offered in one of two configurations: 1) Monolithic, in which the optical head and electronics are combined into a single composite assembly, which is then mounted onto the spacecraft or; 2) Disparate, in which the electronics and head are accommodated in separate housings.

AST-169/CREATED/R The AST OH line of sight shall be perpendicular to the mounting baseplate of the unit.

AST-343/CREATED/T It shall be possible to operate both ASTs simultaneously for an indefinite period (up to the lifetime requirements in AD-17).

AST-1572/CREATED/R The AST baffle shall be provided by the AST supplier as an integral part of the unit.

AST-1571/CREATED/R The AST OH or Monolithic configuration requirements cited in Section 4.2 shall be understood as being inclusive of the baffle (e.g. mass, envelope etc).

4.2 Mechanical Design and Interface Requirements

4.2.1 Mass AST-173/CREATED/T

The complete unit mass in its flight configuration (i.e. optical head, electronics, connectors, mounts and baffle etc) but excluding the spacecraft mounting bracket shall be less than 3 kg. This shall be verified by mass measurement on the fully assembled unit.

4.2.2 Centre of Gravity AST-175/CREATED/T

The Centre of Gravity (CoG) w.r.t. the unit reference hole shall be provided. This shall be derived from a determination of the CoG on the fully assembled unit.

4.2.3 Envelope AST-177/CREATED/T

The OH unit including mounting feet, connectors and baffle shall not exceed the following dimensions envelope (Diameter x Length): 200 mm x 344 mm. This shall be verified by dimension measurement.

AST-630/CREATED/I,R In the case of a Monolithic configuration, the dimensions defined in AST-177 above shall apply to the whole unit.

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AST-178/CREATED/T In the case of a Disparate configuration, the dimensions shall not exceed the following dimensions envelope (Width x Depth x Height): 260 mm x 200 mm x 100 mm. This shall be verified by dimension measurement.

4.2.4 Unit Attachment The requirements in Section 4.2.4.1 are applicable in respect of the Baseline configuration where the AST Bracket is provided by Prime. The requirements in Section 4.2.4.2 are applicable in respect of the Mandatory Option where the AST supplier provides the AST Bracket

4.2.4.1 Prime Provided Bracket (Baseline) AST-415/CREATED/A,R

The AST (OH or monolithic configuration) shall be directly mounted onto SCM shear walls via Aluminium brackets (brackets are provided by Prime); should the AST chassis/mounting interface be manufactured from materials other than aluminium then the design of the AST shall take into account the resulting differential thermo-elastic effects. If there is a separate EU, it shall be directly mounted to the CFRP shear walls. This shall be taken into account with respect to the unit attachment requirements in AD-17.

AST-1561/CREATED/R A finite element model of the AST shall be provided by the supplier to sufficient detail to allow assessment of the thermo-elastic distortion effects between the AST and the mounting bracket. The FEM shall be sufficiently detailed to allow prime to assess the impact from the thermo-elastic distortion in relation to the measurement performance requirements cited in Section 3.6.2.1.

AST-1566/CREATED/R The FEM requirements in section 3.2.4 of AD-17 shall apply to the FEM provided.

4.2.4.2 AST Supplier Provided Bracket (Mandatory Option) AST-1556/CREATED/I,R

The AST bracket shall support the AST, providing attachment to the SCM shear panel and conforming to the envelope and dimensional constraints defined in Figure 4.2-1.

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Figure 4.2-1: AST Bracket Envelope AST-1558/CREATED/T

Mass of AST support bracket shall not exceed 0.6kg per bracket (including margins).

AST-1559/CREATED/T,A The AST and bracket combined shall have a first frequency, when hard-mounted to the SCM shear panel, of greater than 140Hz. (Analytical margin requirements defined in the GDIR (AD-17) shall apply).

AST-1560/CREATED/R The design of the bracket shall allow alignment of the AST via shimming at the AST to bracket interface. Alignment shimming will be performed at spacecraft level following delivery of the AST and bracket.

AST-1562/CREATED/R Alignment shims shall be full contact peelable shims (each 4mm thickness and 40 micron peel).

AST-1563/CREATED/A The bracket will be rigidly mounted to a CFRP shear wall. The bracket design shall be compatible with the differential thermo-elastic deformation between the panel and the bracket assuming that the panel CTE = 0K and taking into account the worst case temperature environments.

AST-1564/CREATED/R The interface of the bracket onto the panel shall be achieved by means of M5 bolts into inserts provided in the panel.

Thermal Environment Parameter Max Min

Spacecraft Internal Radiative Temperature, Operation (�C) 50 -10

Spacecraft Internal Radiative Temperature, Non-Operation (�C) 50 -30

Spacecraft Internal Radiative Temperature, Start-up min (�C) n/a -30

Spacecraft Closure Panel External Radiative Temperature (�C) 150 -150

Spacecraft Sun Shield External Radiative Temperature (�C) 130 -60 (TBC)1

Solar Flux (W/m2) 1464.0 1316.0

Planet Albedo 0.36 0

Earth Temperature (K) 265.0 3

Space Temperature (K) 3

Interface Temperature Stability (�C/hr) 5 (TBC) 1: This minimum temperature may occur during LEOP and transfer phase sun off pointing manoeuvres

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AST-1565/CREATED/R All mechanical design and environmental requirements specified in the GDIR (AD-17) shall be applicable to the bracket.

4.3 Thermal Design and Interface AST-181/CREATED/T

The maximum thermal dissipation of the entire AST unit (including OH and EU, if applicable) shall not exceed 9.1 W.

AST-635/CREATED/R The actual thermal dissipation characteristics exhibited by the unit shall be provided by the supplier for use in the thermal budget.

AST-1467/CREATED/A,R The thermal control of the OH shall be via radiative heat rejection to the spacecraft internal environment

AST-1495/CREATED/A,R The thermal control of the EU shall be as per GDIR (AD-17) section 3.3.

AST-409/CREATED /T,A

The unit thermal design shall consider the worst case thermal environment. As the AST unit is exposed to the external environment of the spacecraft the enveloping qualification/acceptance temperatures of Table 4.3-1 and Table 4.3-2 are applicable to the Monolithic AST configuration, as well as to the OH element of a Disparate AST configuration, according to the AST-166 definitions. For the EU of a Disparate AST configuration the applicable Qualification/Acceptance temperatures are defined by the GDIR-841. Combinations of these environment parameters that produce the worst case conditions shall be assumed in the unit level thermal analysis.

AST-1573//T,A The thermal characteristics defined in Table 4.3-1 shall be assumed in the evaluation of the Non-Science Phase measurement performance requirements cited in Section 3.6.2.2.

Table 4.3-1: AST Thermal Environment Non Science Phase Performance

Max Min

Spacecraft Internal Radiative Temperature, On Station Measurement (�C) 20.0 -10.0

Spacecraft Closure Panel External Radiative Temperature (�C) -90 -150

Spacecraft Sun Shield External Radiative Temperature (�C) 130 100

Solar Flux (W/m2)1 1464.0 1348.0

Space Temperature (K) 3

On Station Measurement Interface Temperature Stability (�C/hr) 0.1 (TBC) 1: Solar Direction is along the spacecraft Z axis and the solar flux need only be considered if the AST is outside the sun shield shadow.

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AST-1489/CREATED/T,A The thermal characteristics defined in Table 4.3-2 shall be assumed in the evaluation of the Science Phase Measurement Performance Requirements cited in Section 3.6.2.1.

Thermal Environment Parameter

Table 4.3-2: AST Thermal Environment for Science Phase Performance Requirements AST-1431/CREATED/T,A

All temperatures shown in Table 4.3-1 and Table 4.3-2 apply to the acceptance limits of the unit. The supplier shall define unit qualification temperatures based on analysis using the defined environment.

The interface temperature applies to the both conductive interface temperature to which the unit is attached and the internal radiative temperature of the spacecraft to which the unit is exposed.

AST-1433/CREATED/A,R For the Non-Science Phase Measurement performance requirements defined in Section 3.6.2.2, the incidence angle of the flux from the Sun and flux from the Earth can be from any direction and the worst case direction shall be assumed in the analysis. (Including the unit being shadowed by the spacecraft). For the Science Phase Measurement performance requirements defined in Section 3.6.2.1 for any Degraded Performance (as a result of the Degraded Dynamics Range defined in Section 3.5.2.2), the AST will be shadowed from solar flux (and not exposed to any significant Earth flux).

AST-1434/CREATED/A,R The external optical properties of the spacecraft closure panels shall be assumed to have an absorptivity of 0.79 and emissivity of 0.76. The underside of the spacecraft sun shield shall be assumed to have an absorptivity of 0.86 and emissivity of 0.05. All reflections shall be considered to be diffuse. The simplified spacecraft external geometry to be assumed for the thermal analysis is shown in Figure 4.3-1. As the sun shield overhang is not consistent around the circumference of the spacecraft the worst case overhang of the sun shield shall be considered. (i.e., if the AST baffle will extend past the smaller dimension of sunshield (60mm) such that while on-station it will be exposed to solar flux, the shorter dimension shall be used in the modelling. However if the AST baffle will remain within the smaller dimension’s shadow the larger sun shield dimension (200mm) shall be used, as this will provide the worst radiative interface environment).

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773.0mm

Sun shield Overhang max 200.0mm min 60.0mm

711.0mm

Sun Shield

Closure Panel

+Zspacecraft

AST Baffle Hole

AST Baffle Hole

Figure 4.3-1: Spacecraft External Geometry For Thermal Analysis AST-636/CREATED/T,A

The above thermal environment applies to the OH or for Monolithic configurations (i.e. including EU). The thermal environment defined in AD-17 section 4.3.3 (GDIR) shall apply to any separate electronics unit that is internal to the spacecraft.

AST-411/CREATED/T,A,R The On-ground thermal requirements specified in AD-17 section 4.3.1 (GDIR) shall apply.

AST-412/CREATED/R The surfaces of the AST that are internal to the spacecraft shall ensure a sufficient heat rejection capability with a high emissivity finish (� >= 0.8). The selection of this and the remaining external finishes shall be made in consultation with the spacecraft prime contractor.

AST-413/CREATED/R The design and supply of any thermal hardware required to maintain the units(s) within the thermal environments specified shall be the responsibility of the equipment supplier.

4.4 Electrical Design and Interface

4.4.1 Power Consumption AST-567/CREATED /T,A

The total power consumption required to operate any single unit during any mission phase and in the presence of the thermal environment range defined in Section 4.3 shall not exceed 9.1 W.

AST-651/CREATED/R The power consumption of the unit while in Standby mode shall be provided by the supplier at the time of the proposal.

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4.4.2 Power Interface AST-569/CREATED/R

The AST is designated a Platform Equipment and shall draw power from the current limited, externally switched 28V regulated power bus as defined in section 3.5.2.1 of AD-17.

AST-570/CREATED/R In the case of a separate electronics and sensor head, only the electronics shall interface to the regulated power bus.

The above requirement means that in the case that the AST comprises separate electronics and optical head, then any power required by the optical head must be drawn from the AST electronics and not the external spacecraft power supply.

4.4.3 Harness All power and signal interfaces between the AST and other units and subsystems will be made via the harness subsystem.

AST-573/CREATED/R The AST shall interface with other units and subsystems via connectors only (i.e. no flying leads of any description).

AST-574/CREATED/R In the case that the AST comprises separate electronics and sensor head, then they shall interface with one another via connectors only (i.e. no flying leads of any description).

AST-575/CREATED/R In the case that the AST comprises separate electronics and sensor head, then the harness connecting the head to the electronics, up to a maximum length of 2 m, shall be provided by the AST supplier.

AST-576/CREATED/T,A In the case that the AST comprises separate electronics and sensor head, then both the head and the electronics shall be compatible with a harness up to 2 m in length.

4.4.4 Interface to Satellite Data Handling AST-578/CREATED/R

The AST shall provide digital interfaces to the Satellite Data Handling system that are compliant to EITHER MIL-STD-1553B OR UART Serial Link (RS422) interfaces (as defined below).

Note There is a strong preference for MIL-STD-1553B.

4.4.4.1 MIL-STD-1553B Interface AST-580/CREATED/R

The signal and command interface shall be via a MIL-STD-1553B interface.

AST-581/CREATED/R The AST shall be a remote terminal (RT) on the 1553B bus as defined in AD-19.

The On Board Computer (OBC) will be the Bus Controller (BC) as defined in AD-19. Furthermore, the only communication with the AST will be from/to the OBC, i.e. there will be no RT to RT communication and the AST will never be required to be the BC.

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AST-583/CREATED/T,R The AST electronics (both main and redundant) shall interface with both the main (A) 1553B data bus and the redundant (B) 1553B data bus.

AST-584/CREATED/T,R The electrical interface and implementation shall comply with the requirements defined in section 3.5.5.1 of AD-17.

AST-585/CREATED/T,R The AST shall be implemented as a non-packet terminal unless this is standard functionality of the unit.

AST-586/CREATED/T,R For telecommands from the OBC to the AST (BC to RT), the message format shall comply with that defined in AD-19 for BC to RT Transfer.

AST-587/CREATED/T,R For transfer of telemetry from the AST to the OBC, the message format shall comply with that defined in AD-19 for RT to BC Transfer.

4.4.4.2 UART Serial Link AST-589/CREATED /R

The signal and command interface shall be via UART Serial Link interface.

AST-590/CREATED/T,R The electrical interface and implementation shall comply with the requirements defined in section 3.5.5.3 of AD-17.

4.4.5 Test Equipment AST-607/CREATED/R

Electrical ground support equipment (EGSE) that generates the electrical stimulation signals shall be provided by the supplier of the AST.

AST-592/CREATED/T,R The AST shall provide an interface to enable stimulation of the AST electronics to support closed loop testing at both subsystem and spacecraft level.

AST-620/CREATED/R In the case of a unit where a single combined AST Optical head and electronics unit is provided it shall be possible to operate the electronics in isolation from the AST head and connect the electronics to the EGSE.

AST-596/CREATED/R The blanking caps for the stimulation interface connector shall be removable.

AST-597/CREATED/R The AST shall meet all of the requirements specified herein with a test harness, 5m in length, connected to the AST test connector.

This harness will be connected to the spacecraft skin connector.

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AST-599/CREATED/T,R The presence of the stimulation interface when no stimulation is applied shall not affect the performance of the AST.

AST-600/CREATED/T,R At spacecraft level, the test harness cited in requirement AST-597 will be connected to the AST electronics stimulation interface and routed to the spacecraft skin connector. This harness, which may be up to 5m (TBC) long, may be left in situ for flight and therefore the AST shall meet the requirements of this specification with this harness in situ.

AST-601/CREATED/R Requirements for termination of the in situ test harness shall be defined by the supplier.

AST-602/CREATED/T,R The AST stimulation interface circuits shall be compatible with a test harness of 30m, length between the test equipment and the skin connector.

AST-603/CREATED/T,A,R The stimulation signal shall be independent of the sensor signal so that no compensation will be required for ground test.

AST-608/CREATED/I,R The AST EGSE shall be capable of stimulating both the AST A electronics unit and the AST B electronics unit simultaneously.

AST-621/CREATED/R In the case of a unit containing 2 optical heads and a single electronics unit, the EGSE and stimulation interface shall support simultaneous test of both units.

AST-609/CREATED/R The AST EGSE shall provide the capability to stimulate the AST electronics unit with simulated AST optical head outputs (the AST optical heads will only be used for sign verification purposes).

AST-610/CREATED/R The AST EGSE shall perform the following tasks: (a) Receive a quaternion that defines the three axis attitude of the AST (and spacecraft body rates, expressed in the AST Measurement Reference Frame, if required) from a simulation of the spacecraft hosted on an external computer (b) Generate a high fidelity image of the stars lying inside the FoV of the AST that is commensurate with the three axis attitude cited above (i.e. simulate the continuous integration process of the detector, for example by providing discrete summations of detector pixel data calculated from each simulation model output). (c) Transmit to the AST electronics the image of the stars lying inside the FoV.

AST-611/CREATED/T,A,R The AST EGSE representation of the AST head output shall provide full modelling of all effects influencing AST performance to sufficient accuracy in the context of the requirements to be met in this specification.

AST-614/CREATED/R The AST EGSE shall represent the AST head performance from beginning to end of life.

AST-612/CREATED/R The AST EGSE output rate shall be consistent with the data output rate from the real AST head.

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AST-613/CREATED/R The AST EGSE shall accept input as cited in point (a) of AST-610 at a frequency of up to 40 Hz.

AST-615/CREATED/R The AST EGSE shall be mechanically and electrically independent of the AST.

AST-616/CREATED/R The AST EGSE shall have an Ethernet interface for the purposes of communicating all data with the Core EGSE (CCS).

AST-617/CREATED/R It shall be possible to configure (i.e. start, stop, pause, initialise etc) the AST EGSE remotely via an Ethernet interface.

AST-618/CREATED/R The AST supplier shall provide the optical ground support equipment (OGSE) necessary for the optical stimulation of a single AST head for open loop AOCS testing and output sign verification purposes.

AST-619/CREATED/R The AST shall provide a mechanical interface to enable mounting of a static optical stimulator on both the optical head and the baffle. This stimulator will be used for output sign verification to support open loop subsystem testing.

AST-1568/CREATED/R AD-22 EGSE Overall Requirements Specification shall be applicable to the AST EGSE requirements presented in Section 4.4.5.

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5. GENERAL DESIGN AND INTERFACE REQUIREMENTS

5.1 General AST-1438/CREATED/A,R

The AST shall be designed to withstand the environmental requirements specified in AD-17. See details in GDIR Applicability Matrix Section 9.

AST-1439/CREATED/T,R The AST shall comply to the general design requirement of AD-17. See details in GDIR Applicability Matrix Section 9.

5.2 Mechanical AST-1441/CREATED/T,R

The AST shall comply to the mechanical design requirements of AD-17. See details in GDIR Applicability Matrix Section 9.

5.3 Thermal AST-1443/CREATED/T,R

The AST unit shall comply to the Thermal design requirements of AD-17. See details in GDIR Applicability Matrix Section 9.

5.4 Electrical AST-1445/CREATED/T,R

The AST shall comply to the Electrical design requirements of AD-17. See details in GDIR Applicability Matrix Section 9.

AST-1446/CREATED/R Tight control over DC and AC magnetic and electric fields at the experiments is essential for the successful achievement of the mission objectives. Critical frequencies span the range .01 milliHz to 10 kHz. Rigorous, documented application of good design practices shall be employed to minimize unit-generated fields at the experiments including careful frequency planning and design analysis to eradicate the generation of spurious frequencies in the bands of interest. Fields, field gradients and fluctuation of fields over time are all important parameters. It is important that frequencies not required for system level use are not allowed to radiate or conduct from the AST to avoid the risk of beat frequencies being generated with other signals. For magnetic fields good design practices include employing minimum currents and loop areas on circuit boards and in wiring, including the use of twisted pairs as appropriate. Strict avoidance of all magnetic materials is essential except where required for correct functioning of the unit. All potential applications of such materials shall be reported to prime before use. For electric field reduction, the minimization of voltages, close proximity of live and return wires and employment of good shielding practices at board level, unit level and in wiring shall all be employed.

AST-1447/CREATED/T The magnetic moment of the unit shall be measured and shall be less then 50 mAm^2 (for the OH) and 50 mAm^2 (for the EU) or 75 mAm^2 for a Monolithic configuration.

AST-1448/CREATED/T Stability of magnetic field and magnetic field gradient to within 0.5%/sqrt(Hz) (TBC) must be demonstrated.

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AST-1449/CREATED/T Measurements of stability shall be made over a 1000 second period (TBC).

AST-1450/CREATED/T The above requirements shall be met in all modes of operation although the stability requirements only apply during measurement modes of the experiments.

AST-1451/CREATED/T Magnetic measurements shall be made in a appropriately compensated facility to ensure that effects due to the Earth's field are negated.

AST-1452/CREATED/T To ensure that sufficient information is available for the spacecraft magnetic model, measurements shall be made of the magnetic field at various positions relative to the test item. These may comprise a series of measurements at a fixed distance from the unit and at equal angles to cover a complete revolution around the item; alternatively measurements may be made at several distances from each face of the item, a suggested minimum set of such measurement ranges being 0.1, 0.3, 0.5 and 1 metre, although the calculation of magnetic moment could be based solely on the 1 metre measurements. The proposed method must be agreed by prime in advance to ensure that sufficient data is provided for the overall spacecraft analysis.

AST-1453/CREATED/T,A An analysis shall be performed to predict the levels of DC and AC electric and magnetic fields from the AST, at a distance of 0.5m from the unit's geometric centre ( i.e. at the experiment test masses) with appropriate use of testing to identify or confirm the results. The following table (Table 5.4-1) gives specific requirements for DC and AC electric and magnetic fields from the AST. Other measurement distances are acceptable providing the results can be shown to be correctable to a distance of 0.5m.

Parameter Value DC Magnetic Field Meeting the dc magnetic field requirements shall be achieved by compliance with

the magnetic moment requirement for the unit of not greater than 50 mAm^2 (for the OH) and 50mAm^2 (for the EU) or 75 mAm^2 for Monolithic configuration, which shall be measured as detailed above.

DC Magnetic Field Gradient

Meeting the dc magnetic field gradient requirements shall be achieved by compliance with the magnetic moment requirement for the unit of not greater than 50 mAm^2 (for the OH) and 50 mAm^2 (for the EU) or 75 mAm^2 for a Monolithic configuration, which shall be measured as detailed above.

AC Magnetic Field For frequencies below 10 kHz the magnitude of a high frequency magnetic field shall be less than 100 nT at 0.5 metres from the field generator This is in addition to the field stability requirement detailed above.

AC Magnetic Field Gradient

For frequencies below 10 kHz the magnitude of a high frequency magnetic field gradient shall be less than 675 nT/m at 0.5 metres from the field generator This is in addition to the field gradient stability requirement detailed above.

Table 5.4-1: Magnetic Fields

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5.5 Identification & Marking AST-1456/CREATED/R

A nameplate shall mark the unit hardware in order to achieve configuration traceability. The identification shall be made in accordance with the requirements of AD-14 section 3.14.

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6. VERIFICATION REQUIREMENTS AST-1458/CREATED/T

Equipment verification shall be performed in accordance with the detailed requirements contained within the specification and AD-14, AD-15 and AD-17.

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7. PRODUCT ASSURANCE REQUIREMENTS AST-1460/CREATED/R

The AST shall be designed, manufactured and tested in accordance with the PA requirements specified in AD-14 and AD-15.

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8. ACRONYMS Acronyms are defined in [AD-21]. Additional acronyms are as follows: AST Autonomous Star Tracker CCD Charge Coupled Device CoG Centre of Gravity EU Electronics Unit FDIR Failure Detection, Isolation and Recovery FoV Field of View OH Optical Head PPS Pulse Per Second PSD Power Spectral Density RMS Root Mean Square TC Telecommand

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9. GDIR APPLICABILITY MATRIX The following table lists the applicable requirements of the GDIR. It contains, in the first column, the Local ID for each applicable GDIR requirement number. The second column contains the GDIR Requirement number and the opening text of the requirement. The third column defines the Applicability Y/N The final column shows the intended verification method

Req No. Reference Applicability Verif. Method

3 General Design and interface Requirements 3.1 General Design Requirements 3.1.1 Lifetime AST-663 GDI-31:

The on-ground lifetime of flight hardware is defin ... Y R

AST-664 GDI-32: The Unit shall meet the requirements of this speci ...

Y A,R

AST-665 GDI-33: The in-orbit lifetime of the satellite is defined ...

Y R

AST-666 GDI-34: The unit shall be designed with positive margins o ...

Y A,R

AST-667 GDI-35: Maintenance during storage shall be as limited as ...

Y R

3.1.2 Design Safety AST-669 GDI-37:

The unit shall be designed and fabricated with com ... Y A

AST-670 GDI-38: General safety requirements for units are as follo ...

Y A

3.1.3 Venting AST-672 GDI-41:

The unit shall be able to operate within a pressur ... Y A,R

AST-673 GDI-42: For all relevant thermal hardware, explicitly MLI, ...

Y R

AST-674 GDI-43: Unless a cavity is hermetically sealed adequate me ...

Y R

AST-675 GDI-44: Structural members (honeycomb panels, in particula ...

Y T,A

3.1.4 Interchangeability AST-677 GDI-46:

All spacecraft units of the same part or configura ... Y R

3.1.5 Identification & Marking AST-679 GDI-50:

For the particular case of connector identificatio ... Y I

3.1.6 Accessibility/Maintainability AST-681 GDI-52:

The design of the unit, the position of the connec ... Y R

AST-682 GDI-53: The equipment shall be designed to require a minim ...

Y R

AST-683 GDI-54: No field maintenance, servicing or adjustment shal ...

Y R

3.1.7 Transportation, Handling and Storage 3.1.7.1 Thermally Conductive Materials AST-686 GDI-70:

Unless justified and agreed beforehand, any therma ... Y I,R

3.1.7.3 Seals

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AST-688 GDI-75: Any seals used shall comply with all the applicabl ...

Y R

AST-689 GDI-76: Any seals requiring periodic replacement during gr ...

Y R

3.1.7.4 Lubricants and Sealants AST-691 GDI-78:

No lubricants shall be used without the prior writ ... Y R

3.1.7.5 Screw Locking AST-693 GDI-80:

All fasteners used on the unit shall be locked by ... Y I,R

3.2 Mechanical Design and Interface Requirements AST-695 GDI-82:

All drawings, specifications and engineering data ... Y R

AST-696 GDI-83: Units shall be compatible with mechanical testing. ...

Y R

AST-697 GDI-84: Following testing the unit shall be inspected to c ...

Y I

AST-698 GDI-87: No unit shall generate microvibration loads at its ...

Y A,R

AST-699 GDI-2058: This Requirement has been Deleted. ...

Y A,R

3.2.1 Structural Design 3.2.1.1 General Requirements AST-702 GDI-91:

The following failure modes, for units at all leve ... Y A

AST-703 GDI-92: The unit shall be designed to withstand the enviro ...

Y A,R

AST-704 GDI-93: For sine and random vibrations, the mechanical siz ...

Y A

AST-705 GDI-94: Wherever practical a fail safe design based on red ...

Y A

AST-706 GDI-95: In cases where a failsafe design cannot be impleme ...

Y A

AST-707 GDI-2045: All potential fracture critical items shall be sub ...

Y A

3.2.1.2 Mass properties AST-709 GDI-98:

All mass estimations shall be accompanied by the d ... Y T

AST-710 GDI-100: The mass of an item must be measured with the foll ...

Y T

3.2.1.3 Centre of Gravity and Moment of Inertia AST-712 GDI-102:

All COG and MOI estimates shall be accompanied by ... Y A

AST-713 GDI-104: The unit centre of gravity shall be determined wit ...

Y T,A

AST-714 GDI-105: The unit moment of inertia shall be determined wit ...

Y A

3.2.1.4 Stiffness requirement AST-716 GDI-113:

Unless otherwise specified, units shall have their ... Y T,A

AST-717 GDI-114: The stiffness requirements shall be demonstrated t ...

Y T,A

3.2.1.5 Strength Requirements 3.2.1.5.1 Definitions and General Requirements

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AST-720 GDI-117: The design load factor philosophy of the LISA PF s ...

Y A

AST-721 GDI-2077: LPF mechanical testing shall take into account an ...

Y T

AST-722 GDI-2076: LPF mechanical testing shall take into account a Q ...

Y T,A

AST-723 GDI-2057: An additional Protoflight Factor of Safety, FOSPF ...

Y T,A

AST-724 GDI-129: The units shall be designed with positive margins ...

Y A

AST-725 GDI-130: The design loads for the structure elements are to ...

Y A

AST-726 GDI-131: The internal loads (thermo elastic, pre-stressed m ...

Y A

AST-727 GDI-132: For the computation of the design loads the maximu ...

Y A

3.2.1.5.2 Margin Of Safety & Safety Factors AST-729 GDI-2121:

For all Lisa-Pathfinder elements the design factor ... Y A

AST-730 GDI-2120: Where design loads are generated using FE analyses ...

Y A

AST-731 GDI-136: The LPF hardware shall be able to withstand, witho ...

Y A,R

AST-732 GDI-137: All mechanical elements shall demonstrate positive ...

Y T,R

AST-733 GDI-147: The margins of safety for all elements of the unit ...

Y A

AST-734 GDI-148: All bolts shall be sized to prevent sliding under ...

Y A

AST-735 GDI-149: Wherever applicable, rules for general design of b ...

Y R

AST-736 GDI-150: In addition, in case of combined loads due to ther ...

Y A

AST-737 GDI-153: Method for evaluation of dimensioning loads/stress ...

Y A

3.2.2 Design Requirements 3.2.2.1 Attachment Requirements AST-740 GDI-160:

For the preliminary determination of the requested ... Y A

AST-741 GDI-161: The attachment points shall provide a controlled s ...

Y I,R

AST-742 GDI-162: The interface plane flatness of a unit shall be be ...

Y I

AST-743 GDI-163: The mechanical mounting interface shall be consist ...

Y R

AST-744 GDI-164: The unit bolts type and number shall be defined to ...

Y R

AST-745 GDI-165: Unless otherwise specified all units shall be thro ...

Y I,R

AST-746 GDI-2132: To minimise CoG uncertainty of the unit when mount ...

Y I,R

AST-747 GDI-167: Thermally dissipative units shall have proper prov ...

Y I,R

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AST-748 GDI-168: Unless special conditions override, the thickness ...

Y I,R

AST-749 GDI-169: For the unit mounting, provision shall be made for ...

Y I,R

AST-750 GDI-2123: Unit Lug/Hole Design Requirements: Unit mounting h ...

Y I,R

AST-751 GDI-170: Sufficient clearance shall be allowed between mech ...

Y I,R

AST-752 GDI-171: Fasteners shall be verified similarly to other str ...

Y A

AST-753 GDI-173: Fasteners shall be procured and tested according t ...

Y I

AST-754 GDI-174: The Flight equipment shall be able to survive:- - ...

Y A

AST-755 GDI-176: Units requiring alignment with an accuracy better ...

Y R

AST-756 GDI-177: Optical references are required to withstand all t ...

Y R

AST-757 GDI-178: Location of optical references for units shall be ...

Y R

AST-758 GDI-179: The alignment errors shall be included in pointing ...

Y R

AST-759 GDI-180: Units which require alignment accuracy of ±0.25° o ...

Y R

3.2.3 Mechanical / Optical Interface Control Documents AST-761 GDI-183:

The mechanical and optical configuration and its i ... Y A

AST-762 GDI-184: Interfaces will be subjected to a formal inspectio ...

Y T,I

AST-763 GDI-185: The issues of ICDs have to be released as defined ...

Y A

AST-764 GDI-186: One of the attachment holes on a unit shall be spe ...

Y R

AST-765 GDI-187: The unit reference frame shall have its origin at ...

Y R

AST-766 GDI-188: The unit alignment reference frame shall have its ...

Y R

AST-767 GDI-190: The dimensioning of the attachment hole pattern sh ...

Y A

AST-768 GDI-191: Interface Control Drawings shall be provided to th ...

Y R

3.2.4 Mechanical Mathematical Model Requirements AST-769 GDI-197:

Finite elements models shall be provided for all i ... Y A

3.2.4.1 Software/Electronic Files Delivery AST-1498 GDI-200:

The model shall be prepared using NASTRAN Software ... Y R

AST-1499 GDI-201: Finite elements models shall be provided for all u ...

Y R

AST-1500 GDI-202: For the FEM delivery, the following list of inform ...

Y R

3.2.4.2 Units

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AST-1502 GDI-204: S.I. units are to be used: · Newton (N) for force ...

Y R

3.2.4.3 Coordinate system AST-1504 GDI-206:

The FEM shall use the Units/assembly Reference Fra ... Y R

3.2.4.4 Model Identity/Comment AST-1506 GDI-208:

The model name, issue and date must be included at ... Y R

AST-1507 GDI-209: The model description shall refer to a configured ...

Y R

AST-1508 GDI-210: The following comment cards must be included in th ...

Y R

3.2.4.5 Model Size and Identification Numbering AST-1510 GDI-212:

Numbering of BULK data cards: Each Nastran BULK ca ...

Y R

AST-1511 GDI-213: Excluded BULK data cards: All data cards used to d ...

Y R

AST-1512 GDI-214: The authorised NASTRAN elements are the following: ...

Y R

AST-1513 GDI-215: The use of MSG-MESH data cards is prohibited. A pu ...

Y R

AST-1514 GDI-216: Structural and equipment masses: For the structura ...

Y R

AST-1515 GDI-217: When necessary, equipments may be represented by C ...

Y R

3.2.4.6 FEM Checks 3.2.4.6.1 Mass Distribution Check AST-1518 GDI-221:

The outputs of the NASTRAN “Grid Point Weight Gene ... Y A

3.2.4.6.2 Strain Energy and Max Ratio Check AST-1520 GDI-223:

Strain energy and stiffness maxratio are requested ... Y A

3.2.4.6.3 Conditioning Checking AST-1522 GDI-225:

The purpose of the conditioning check is to identi ... Y A

3.2.4.6.4 Constraint Check AST-1524 GDI-227:

The purpose of the constraint check is to verify t ... Y R

3.2.4.6.5 "Free-Free" Check. AST-1526 GDI-229:

The purpose of the "Free-Free" check is to verify ... Y R

3.2.4.6.6 Static Load Check AST-1528 GDI-231:

The purpose of the static load check is to confirm ... Y R

3.2.4.6.7 "Zero" Stress Thermo-elastic Check AST-1530 GDI-233:

The purpose of the "Zero" stress check is to verif ... Y R

3.2.4.7 FEM correlation.

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AST-1532 GDI-235: Full finite element models shall be correlated wit ...

Y T,A

AST-1533 GDI-2102: For modes with effective masses > 10% of the total ...

Y T,A

AST-1534 GDI-2101: Damping shall take measured values as input for th ...

Y R

AST-1535 GDI-2100: The cross-orthogonality checks shall comply with; ...

Y T,A

AST-1536 GDI-2099: For other significant modes, · MAC shall be > 0.85 ...

Y T,A

AST-1537 GDI-2098: For modes with effective masses >10%of the total m ...

Y T,A

AST-1538 GDI-2097: For fundamental modes, · MAC shall be > 0.95 · Eig ...

Y T,A

AST-1539 GDI-2096: The difference between the Centre of Gravity posit ...

Y T,A

AST-1540 GDI-2095: The mass difference between the measured and FEM f ...

Y T,A

3.2.5 Gravitational Mathematical Model Requirements AST-771 GDI-2043:

For gravitational modelling purposes, the mass dis ... Y A,R

3.3 Thermal Design and Interface Requirements 3.3.1 Definition of Temperatures and Terms 3.3.1.1 Radiatively Controlled Unit AST-775 GDI-239:

In the frame of LISA Pathfinder, all units with th ... Y R

3.3.1.2 Conductively Controlled Unit AST-777 GDI-241:

All units with a power density on the total skin h ... Y R

3.3.1.3 Isothermal Unit AST-779 GDI-243:

As far as possible thermal gradients across the ba ... Y R

AST-780 GDI-244: For radiative units the temperature difference bet ...

Y R

AST-781 GDI-245: For conductive units the temperature difference be ...

Y R

AST-782 GDI-246: For non-isothermal units a reference temperature s ...

Y R

3.3.1.4 Temperature Reference Point (TRP) AST-784 GDI-248:

The temperature reference point (TRP) shall be sel ... Y R

3.3.2 Thermal Interface Requirements 3.3.2.1 Conductive Interface AST-787 GDI-252:

The mounting interface shall comply with the mecha ... Y A

AST-788 GDI-253: Unit mounting areas shall not be painted or anodis ...

Y R

AST-789 GDI-254: All units shall have a smooth and plane baseplate ...

Y R

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AST-790 GDI-255: Local heat flux shall not be greater than 1.5x spe ...

Y A

3.3.2.2 Radiative Interface AST-792 GDI-258:

Units shall be designed with an emittance > 0.8 (b ... Y R

3.3.2.3 Internal Temperature Monitoring AST-794 GDI-260:

Temperature monitoring of selected points within a ... Y R

AST-795 GDI-261: The location, type and electrical interface of all ...

Y R

3.3.3 Thermal Design Requirements AST-797 GDI-263:

The units shall be designed such that all internal ... Y A

AST-798 GDI-264: Hot spots on the external surface of the unit are ...

Y A,R

AST-799 GDI-2079: Average dissipation of the unit operating with sta ...

Y A,R

3.3.4 Thermal Control AST-801 GDI-267:

All thermal hardware mounted on the unit shall be ... Y R

3.3.5 Thermal Interface Control Documents AST-803 GDI-269:

All unit thermal interfaces shall be described wit ... Y R

3.3.6 Thermal Mathematical Model Requirements 3.3.6.1 Thermal Interface Modeling AST-806 GDI-2091:

The use of the ESARAD and ESATAN software packages ... Y A,R

AST-807 GDI-272: The Thermal mathematical model shall be provided f ...

Y A

AST-808 GDI-273: Units: All units used in thermal models (geometric ...

Y A

3.3.6.2 Thermal Model Correlation AST-810 GDI-275:

The detailed thermal model of a unit shall be veri ... Y T,A

3.3.6.3 Reduced Thermal Model AST-812 GDI-277:

The consistency between reduced and detailed therm ... Y A

AST-813 GDI-278: The convergence of the thermal models shall be dem ...

Y A

3.4 Optical Design and Interface Requirements 3.4.1 Optical Design Requirements 3.4.1.1 General Optical Design AST-817 GDI-282:

For each optical surface, the physical dimension s ... Y R

3.4.1.2 Materials AST-819 GDI-284:

Glass types and material quality shall be selected ... Y R

AST-820 GDI-285: The use of stain sensitive glasses shall be avoide ...

Y R

AST-821 GDI-286: The use of optical cements shall be avoided as far ...

Y R

3.4.1.3 Coatings

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AST-823 GDI-289: Metallic layers of the coatings, if any, shall be ...

Y R

AST-824 GDI-290: Thermo-optical properties of the coatings shall be ...

Y R

AST-825 GDI-292: High efficiency anti-reflective coatings shall be ...

Y R

AST-826 GDI-293: Sensitivity of coatings to polarisation effects as ...

Y T,R

3.4.1.4 Performances AST-828 GDI-295:

The optical performance of the unit shall be verif ... Y T

AST-829 GDI-296: Alignment and interface with regard to other optic ...

Y T

3.4.2 Optical Interface Requirements AST-831 GDI-298:

The unit supplier shall provide the optical interf ... Y R

AST-832 GDI-299: The free mechanical aperture of optical surfaces s ...

Y R

AST-833 GDI-300: In addition to specific requirements mentioned in ...

Y R

3.4.3 Optical Mathematical Model Requirements AST-835 GDI-302:

The unit supplier shall use an optical model for n ... Y A

AST-836 GDI-303: The numerical model shall be developed in Code V ® ...

Y A

3.5 Electrical Design and Interface Requirements 3.5.1 General Requirements AST-839 GDI-308:

All electrical performances are specified under Wo ... Y R

AST-840 GDI-309: Beginning-Of-Life criteria shall be derived by the ...

Y R

AST-841 GDI-2024: All PROM's shall be accessible and removeable afte ...

Y R

3.5.2 Power Interface Requirements (LC & FC) AST-843 GDI-2046:

The design of all essential loads (i.e those suppl ... Y A,R

3.5.2.1 Sunlight Regulated Power Requirements AST-845 GDI-338:

All units connected to the sunlight regulated bus ... Y T,A

AST-846 GDI-2104: The spacecraft sunlight regulated bus shall have a ...

Y T,R

AST-847 GDI-2103: For load changes of up to 50% of the nominal load ...

Y T,R

AST-848 GDI-2133: The bus voltage shall remain within 5% of its nomi ...

Y T,R

AST-849 GDI-339: If undervoltage protection is implemented by the l ...

Y T

AST-850 GDI-340: In case of an inductive load, when considering the ...

Y T,A

AST-851 GDI-341: The load shall not be irreversibly degraded for an ...

Y R

AST-852 GDI-342: No fuse protection shall be implemented. ...

Y R

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AST-853 GDI-343: Primary current protection shall not be implemente ...

Y R

AST-854 GDI-344: The contractor shall design the load side of the L ...

Y T,R

AST-855 GDI-346: All power converters shall be designed to allow op ...

Y T

AST-856 GDI-347: The free-running frequency shall be limited to ±10 ...

Y T

AST-857 GDI-348: The as designed free-running frequency and frequen ...

Y T

AST-858 GDI-349: Units connected to LCL's or FCL's shall be designe ...

Y A

AST-859 GDI-1273: At the point of regulation, the impedance of the v ...

Y T,R

AST-860 GDI-352: The contractor shall design his side of the Regula ...

Y T,R

AST-861 GDI-354: Following switch-ON, and during input filter charg ...

Y T,R

3.5.2.2 Power Consumption Requirements AST-863 GDI-361:

The compliance versus the power allocations shall ... Y T,A

AST-864 GDI-362: For each power interface circuit, the following co ...

Y T,A

AST-865 GDI-363: A power consumption test shall be required at temp ...

Y T,R

3.5.2.3 Tolerance to Power Bus Failures AST-867 GDI-365:

When a unit is internally redundant, and the suppl ... Y T,A

3.5.2.4 Initial Electrical Status AST-869 GDI-367:

Upon application of power in nominal conditions al ... Y T

3.5.2.5 Special Case: Secondary Power Supplied Units AST-871 GDI-370:

It shall be possible to switch on the source unit ... Y T

AST-872 GDI-371: The source unit shall be protected against short-c ...

Y T

AST-873 GDI-372: The supplied unit and Electrical I/F shall withsta ...

Y T,A

3.5.3 Standard Signals 3.5.3.1 General Conventions AST-876 GDI-378:

Specified driver (or source) characteristics shall ... Y R

AST-877 GDI-379: All data and signal interface drivers shall surviv ...

Y T,A

AST-878 GDI-380: The unit shall tolerate active signal I/Fs when un ...

Y T,A

AST-879 GDI-381: In case the electrical architecture does foresee c ...

Y T,R

AST-880 GDI-382: In case no load is specified, the characteristics ...

Y R

3.5.3.2 Harness Capacitance AST-882 GDI-391:

Interface signal drivers shall consider the capaci ... Y A

3.5.4 Connectors General Design Requirements

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3.5.4.1 Harness AST-885 GDI-395:

Cables falling into different EMC classifications ... Y I,R

AST-886 GDI-396: All cable bundles shall be routed as close as poss ...

Y I,R

AST-887 GDI-397: In wiring through connectors all leads shall be ke ...

Y I,R

AST-888 GDI-398: The DC resistance between the single cable shield ...

Y T

AST-889 GDI-399: The structure termination of shields shall be made ...

Y I,R

3.5.4.2 Connector Types AST-891 GDI-401:

All connectors mounted on units shall be D*MA** co ... Y R

AST-892 GDI-402: All flight connectors shall be designed to withsta ...

Y I,R

AST-1541 GDI-2158: Individual mate/demates shall be recorded in a mat ...

Y R

AST-1542 GDI-2157: The number of times flight connectors are mated / ...

Y R

AST-1543 GDI-2156: If by prior agreement with ASU the number of mates ...

Y I,R

AST-893 GDI-403: Different connector classes shall be implemented i ...

Y R

3.5.4.3 Connector Characteristics AST-895 GDI-405:

Connectors at interfaces shall be clearly identifi ... Y R

AST-896 GDI-406: Connectors shall not be a source of single point f ...

Y R

AST-897 GDI-407: Equipment or structure-mounted connectors shall be ...

Y R

AST-898 GDI-408: Male and female connectors shall be mechanically l ...

Y R

AST-899 GDI-409: Active lines together with their return shall be o ...

Y I

AST-900 GDI-410: Connectors shall be made of Non magnetic material ...

Y R

AST-901 GDI-411: For any unit connector which contains a number of ...

Y T,R

AST-902 GDI-412: Nominal and redundant lines shall have separated c ...

Y R

3.5.4.4 Connector Mounting AST-904 GDI-414:

All electrical connectors shall be located at a mi ... Y R

AST-905 GDI-415: Connectors shall be arranged in such a way that th ...

Y R

AST-906 GDI-416: Mechanical methods in conjunction with identificat ...

Y I,R

AST-907 GDI-417: Connector savers shall be utilized on all flight s ...

Y R

AST-908 GDI-418: The connection shield ground pin to case shall be ...

Y R

3.5.4.5 Test Connectors

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AST-910 GDI-420: Test connectors shall have sufficient protection t ...

Y R

AST-911 GDI-421: Test connectors shall be protected by EMC metal co ...

Y I,R

AST-912 GDI-422: The metallic protection cover shall be capable of ...

Y R

3.5.5 Standard Interfaces 3.5.5.1 MIL-STD-1553 Bus Interfaces (MIL) AST-915 GDI-426:

Each data bus subscriber equipment shall comply wi ... Y R

AST-916 GDI-427: All units (BC or RT) shall be configured in long s ...

Y R

AST-917 GDI-428: Each BC and RT (N&R) shall be connected to both 15 ...

Y R

AST-918 GDI-429: Each stub shall be grounded inside each RT or BC d ...

Y R

AST-919 GDI-430: The RT address shall be programmable on an externa ...

Y R

AST-920 GDI-431: The 1553-bus shall be connected on separate connec ...

Y R

AST-921 GDI-2139: The 1553-bus shall be connected on separate connec ...

Y R

AST-922 GDI-1198: Unless otherwise agreed with the Prime Contractor, ...

Y R

AST-923 GDI-432: The 1553-Bus Protocol shall be compliant to the LI ...

Y R

AST-924 GDI-434: The unit shall be compatible with the setup as def ...

Y R

3.5.5.2 Standard Balanced Digital link (SBDL) AST-926 GDI-438:

The SBDL link interface is dedicated to serial dig ... Y T,R

AST-927 GDI-1201: The contractor shall design his side of the Standa ...

Y T,R

3.5.5.3 UART Serial Link (USL) AST-929 GDI-450:

The UART RS-422 serial link shall be composed of t ... Y R

AST-930 GDI-451: The UART RS-422 Serial Link Interface shall be imp ...

Y R

AST-931 GDI-452: The contractor shall design his part of the UART R ...

Y R

AST-932 GDI-453: Figure GDI-456 shows an example for data transmiss ...

Y R

AST-933 GDI-1274: The OBC shall be able to send commands on the Tran ...

Y T

AST-934 GDI-1275: No data repetition mechanism in both directions sh ...

Y T

AST-935 GDI-1276: Command messsages sent by the OBC to the user and ...

Y T

3.5.5.4 Timing Pulses 3.5.5.4.1 Synchronisation or Datation Pulses (PPS) AST-938 GDI-460:

The Pulse Per Second (PPS) Interface shall be impl ... Y R

AST-939 GDI-462: The active level shall be High level ...

Y R

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AST-940 GDI-463: The synchronisation edge shall be the rising edge ...

Y R

AST-941 GDI-464: The pulse width shall be ³ 900 ns ...

Y T

3.5.5.4.2 Synchronization Clock Interface (TBC) 3.5.5.6 Temperature Acquisitions (ANY, ANP, ANF, ANT) AST-944 GDI-482:

The signal shall be transmitted via twisted shield ... Y R

AST-945 GDI-483: The temperature aquisition interface circuitry, as ...

Y R

3.5.5.6.1 Thermistor Type1: YSI-44907/-44908 (ANY) AST-947 GDI-1215:

Temperature Acquisition Type 1: YSI 44907/YSI-4490 ... Y T,R

3.5.6 Electrical Interface Control Document AST-949 GDI-558:

Interfaces will be formally controlled within the ... Y R

3.5.7 EMC Requirements 3.5.7.1 Bonding AST-952 GDI-562:

The bond shall be resistant against corrosion and ... Y R

AST-953 GDI-563: Metallic parts of each electrical equipment chassi ...

Y T

AST-954 GDI-564: Joint faces shall be flat and clean before assembl ...

Y I,R

AST-955 GDI-566: Each electrical equipment chassis (case) shall be ...

Y T,R

AST-956 GDI-567: Metallic receptacles of connectors shall be electr ...

Y T

3.5.7.1.1 Ground Reference Rail AST-958 GDI-569:

Electrical bonding throughout CFRP structure shall ... Y R

AST-959 GDI-570: The resistance between any adjacent parts of the G ...

Y T,R

AST-960 GDI-571: The resistance between any two points of the GRR s ...

Y T,R

3.5.7.1.2 Cable and Harness Shields AST-962 GDI-573:

Where shielded wires are used, the shield shall be ... Y R

AST-963 GDI-574: The maximum unshielded length of any shielded wire ...

Y R

AST-964 GDI-575: Daisy chaining of shield terminations shall be avo ...

Y R

AST-965 GDI-576: Shields shall not be used as an intentional curren ...

Y R

3.5.7.1.4 Mechanical Parts AST-967 GDI-581:

Mechanical Parts without electrical nor shielding ... Y T,R

AST-968 GDI-582: Mechanical Parts used for electromagnetic shieldin ...

Y T,R

3.5.7.2 Grounding and Isolation 3.5.7.2.1 General AST-971 GDI-585:

Each unit shall provide a grounding point, which i ... Y I

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AST-972 GDI-586: CFRP and SiC shall not be used as an electrical bo ...

Y R

3.5.7.2.2 Electrical and Electronic Unit Requirement AST-974 GDI-588:

The structure of electrical and electronic unit sh ... Y T

AST-975 GDI-589: Openings for drainage, ventilation, etc... shall n ...

Y I

AST-976 GDI-590: All units shall have a M4 bonding stud ...

Y I

AST-977 GDI-591: The design of this bonding stud shall allow the co ...

Y I

3.5.7.2.3 Insulating materials AST-979 GDI-593:

Space exposed insulating material having a bulk re ... Y R

AST-980 GDI-595: MLI: MLI shall carry at least 1 conductive layer ...

Y I

AST-981 GDI-596: MLI: The grounding points shall be in a minimum of ...

Y I,R

AST-982 GDI-597: MLI: The resistance between each bonding point an ...

Y T

AST-983 GDI-598: MLI: The resistance between each bonding point an ...

Y T

AST-984 GDI-599: PAINTS: Refer to Section GDI-592 above. ...

Y R

AST-985 GDI-600: HEATERS & THERMISTORS: Heaters, thermistors and o ...

Y T,R

3.5.7.3 Primary and Secondary Power Lines 3.5.7.3.1 Primary Power Lines AST-988 GDI-605:

Isolation: Within all units the primary power buse ... Y R

AST-989 GDI-606: Isolation: All units (except PCDU) shall maintain ...

Y T,R

3.5.7.3.2 Secondary Power Lines AST-991 GDI-609:

Grounding: All secondary supplies, inside a unit, ... Y I,R

AST-992 GDI-1988: Equipment with its own dedicated DC - DC converter ...

Y T

AST-993 GDI-610: Isolation: prior to connection of the unit interna ...

Y T,R

AST-994 GDI-2106: After grounding, the impedance between the unit se ...

Y T,R

AST-995 GDI-611: Secondaries distributed between units (1 supplier; ...

Y R

AST-996 GDI-612: Secondaries distributed between units (1 supplier; ...

Y R

AST-997 GDI-614: Grounding diagram including zero volts interconnec ...

Y I

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AST-998 GDI-615: The symbols in Figure GDI-2107 below shall be used ...

Y R

3.5.7.3.3 Signal Interfaces AST-1000 GDI-617:

Signal circuits interfacing between Satellite equi ... Y R

AST-1001 GDI-618: Where single-ended signal transmitters are used, i ...

Y R

AST-1002 GDI-619: The use of common signal return paths is only perm ...

Y R

3.5.7.3.4 EGSE Grounding and Isolation AST-1004 GDI-621:

EGSE signal and power circuits interfacing with fl ... Y R

3.5.7.4 Magnetic Moment AST-1006 GDI-1997:

Each equipment shall be designed and fabricated to ... Y T,R

AST-1007 GDI-1998: All equipments shall provide magnetic dipole momen ...

Y T

3.6 Operations Design and Interface Requirements 3.6.1 Bit / Byte Numbering Convention AST-1010 GDI-632:

In all project specific documentation including co ... Y T,R

AST-1011 GDI-634: During file transfer, within any data type structu ...

Y T,R

3.6.2 Operational Functions 3.6.2.1 Handling of Operational Configuration, Modes and

States

AST-1014 GDI-638: Mode/State transitions: Transitions from one mode/ ...

Y R

AST-1015 GDI-639: The unit supplier shall identify appropriate modes ...

Y R

AST-1016 GDI-640: At all times, equipment and units shall be in a cl ...

Y T,R

AST-1017 GDI-641: In addition, modes and the mode transitions manage ...

Y T,R

AST-1018 GDI-642: The unit supplier shall identify all internal and ...

Y R

AST-1019 GDI-643: The unit supplier shall identify all transition ti ...

Y R

AST-1020 GDI-644: Mode/State transitions with duration longer than 1 ...

Y R

AST-1021 GDI-645: It shall be possible to command the unit into each ...

Y T,R

3.6.2.2 Commandability 3.6.2.2.1 General AST-1024 GDI-648:

Commandability is characterised by the set of comm ... Y T

AST-1025 GDI-649: In operating states of the unit, it shall be possi ...

Y T

AST-1026 GDI-650: In addition, in non-operating states of the unit, ...

Y T

AST-1027 GDI-651: Individual switching of switchable elements (e.g. ...

Y T

AST-1028 GDI-652: The on-board reception, processing and execution o ...

Y T,R

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AST-1029 GDI-653: The function of a command shall not change through ...

Y T,R

AST-1030 GDI-654: A single command may be used to initialise a chang ...

Y T,R

AST-1031 GDI-655: Commands with variable bit-fields meaning shall no ...

Y R

AST-1032 GDI-656: Nominal and the redundant functions or equipments ...

Y T

AST-1033 GDI-657: The unit design shall avoid any conflict between a ...

Y T

3.6.2.3 Observability 3.6.2.3.1 General AST-1036 GDI-660:

Observability is characterised by the set of telem ... Y R

AST-1037 GDI-661: The unit shall provide in its housekeeping telemet ...

Y T,R

AST-1038 GDI-662: The unit shall provide the necessary instrumentati ...

Y T,R

AST-1039 GDI-663: Telemetry measurement sensors shall be designed su ...

Y T

AST-1040 GDI-664: It shall be possible to determine the status of th ...

Y T

AST-1041 GDI-665: Essential (high-priority) telemetry data enabling ...

Y T,R

AST-1042 GDI-666: Telemetry shall always be provided to identify una ...

Y T,R

AST-1043 GDI-667: Status information in telemetry shall be provided ...

Y T,R

AST-1044 GDI-668: Any TM processing required at a higher operational ...

Y R

AST-1045 GDI-669: Telemetry shall always be available to determine t ...

Y R

AST-1046 GDI-670: When a key parameter is derived on-board from seve ...

Y T,R

3.6.2.3.2 Telemetry Acquisition AST-1048 GDI-672:

The TM acquisition process by the data bus shall n ... Y T

AST-1049 GDI-673: The unit design shall avoid any conflict between t ...

Y T

AST-1050 GDI-674: TM acquisitions with conditional meaning shall not ...

Y R

AST-1051 GDI-675: The value of a telemetry parameter shall be transm ...

Y R

AST-1052 GDI-676: Analog TM Acquisition: Analog TM acquisitions sha ...

Y T,R

AST-1053 GDI-677: Acquisition of safety critical analog parameters o ...

Y R

AST-1054 GDI-678: The values of currents or voltages readings shall ...

Y R

AST-1055 GDI-679: The calibration curve of an analog parameter shall ...

Y R

3.6.2.3.3 Observability of Hardware Configuration

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AST-1057 GDI-681: At switch on, the configuration of the unit at ele ...

Y T

AST-1058 GDI-682: In case a unit includes several elementary functio ...

Y R

AST-1059 GDI-683: The configuration of any on-board device and any s ...

Y T,R

AST-1060 GDI-684: Any configuration command register shall be observ ...

Y R

AST-1061 GDI-685: The acquisition of the unit configuration/state sh ...

Y R

AST-1062 GDI-686: The acquisition of an ON/OFF status for a relay sh ...

Y R

AST-1063 GDI-687: If the unit controls the redundancy configuration ...

Y T

AST-1064 GDI-688: Nominal and redundant functions shall be observabl ...

Y R

3.6.2.3.4 Observability of Commands AST-1066 GDI-690:

Commands to the unit shall be acknowledged in an u ... Y R

AST-1067 GDI-691: Acknowledgement of commands shall be direct (i.e. ...

Y T,R

AST-1068 GDI-692: The association between command acknowledgement ac ...

Y I

AST-1069 GDI-693: Successful execution of a command to the unit shal ...

Y T,R

AST-1070 GDI-694: Failures in the acceptance and /or the execution o ...

Y T,R

3.6.2.3.5 Converters Observability AST-1072 GDI-696:

Sufficient data to monitor the converters shall be ... Y T

3.6.2.4 Safety Critical and Hazardous Functions AST-1074 GDI-700:

All critical commands shall be identified at equip ... Y A

AST-1075 GDI-701: The execution of any unit command or command seque ...

Y A

AST-1076 GDI-702: Commanding of critical commands shall be implement ...

Y A,R

AST-1077 GDI-703: The status of inhibition of safety critical functi ...

Y T

AST-1078 GDI-704: Units shall provide an unambiguous health status o ...

Y T

3.6.2.5 Handling of Memories AST-1080 GDI-706:

Any part of installed RAM’s shall be readable by m ... Y T

AST-1081 GDI-707: Any part of installed RAM’s shall be overwriteable ...

Y T

AST-1082 GDI-708: Any part of installed ROM’s shall be readable by m ...

Y T

AST-1083 GDI-709: For failure investigation, it shall be possible to ...

Y T

3.6.2.6 Autonomy AST-1085 GDI-711:

Apart from failure situations, the unit shall oper ... Y T

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AST-1086 GDI-712: All parameters used for autonomous operations and ...

Y T

3.6.2.7 Automatic Functions AST-1088 GDI-714:

It shall be possible to inhibit and to override al ... Y T

AST-1089 GDI-715: All actions generated by automatic on-board logic ...

Y T

AST-1090 GDI-716: The automatic function design shall be such that n ...

Y A,R

AST-1091 GDI-717: Telemetry shall be associated to all automatic fun ...

Y T

AST-1092 GDI-718: For all the automatic logic using several criteria ...

Y T

AST-1093 GDI-719: The capability to change all on board logic (hardw ...

Y T,R

3.6.2.8 Time Synchronisation AST-1095 GDI-721:

If the unit has operationally not been synchronise ... Y R

AST-1096 GDI-722: If the unit has the function, all information on h ...

Y R

AST-1097 GDI-723: Timing information provided in Housekeeping teleme ...

Y T,R

3.6.2.9 Fault Management / FDIR 3.6.2.9.1 Unit Fault Protection AST-1100 GDI-726:

Any unit shall be able to withstand (i.e. remain i ... Y T,R

AST-1101 GDI-727: Any unit shall be able to withstand (i.e. remain i ...

Y T,R

AST-1102 GDI-728: It shall be possible to repeat any command several ...

Y T,R

3.6.2.9.2 Unit Self Tests AST-1104 GDI-730:

All units that perform regular self-tests shall re ... Y R

3.6.2.9.3 Failure Detection, Isolation and Recovery (FDIR) Functions

AST-1106 GDI-733: FDIR functions shall be implemented in a hierarchi ...

Y A,R

AST-1107 GDI-734: The unit shall automatically detect any failure, w ...

Y T,R

AST-1108 GDI-735: At unit level failures shall be detectable by adeq ...

Y A

AST-1109 GDI-736: Failure detection algorithms shall report in event ...

Y A,R

AST-1110 GDI-737: Failures which require a reaction time less than 1 ...

Y T,A

AST-1111 GDI-738: Failure which requires a reaction time between 10s ...

Y A,R

AST-1112 GDI-739: Failure isolation shall be performed at switchable ...

Y T,A

AST-1113 GDI-740: Any FDIR actions on unit level shall be reported t ...

Y T,R

AST-1114 GDI-741: The need for intervention of higher levels to reac ...

Y T,A,R

3.6.3 Other Requirements

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3.6.3.1 Inputs to Design Justification File AST-1117 GDI-744:

The unit supplier shall provide a design justifica ... Y R

3.6.3.2 Inputs to Operational Database AST-1119 GDI-746:

The unit supplier shall provide inputs to the Oper ... Y R

AST-1120 GDI-747: Data to be provided (the list is not exhaustive): ...

Y R

3.6.3.3 Operation Manual AST-1122 GDI-749:

The unit supplier shall provide an Operations Manu ... Y R

AST-1123 GDI-750: The following standardization (Table GDI-751) shal ...

Y R

4 Environment Design Requirements 4.1 Atmospheric Conditions 4.1.1 Humidity AST-1127 GDI-771:

The unit shall be designed to withstand a relative ... Y R

4.1.2 Cleanliness AST-1129 GDI-773:

The cleanliness design requirements on the unit H/ ... Y R

4.1.3 Storage time AST-1131 GDI-775:

The S/C units flight H/W shall be designed to with ... Y R

4.1.4 Pressure Environment AST-1133 GDI-780:

Units mounted on the S/C shall be designed to with ... Y T

4.1.5 Contamination AST-1135 GDI-782:

Cleanliness requirements are as defined in the Sec ... Y T,R

4.2 Mechanical Environment 4.2.1 Ground Operations Loads AST-1138 GDI-790:

The equipment/assembly and associated transport co ... Y T,A

AST-1139 GDI-793: During ground transportation the equipments shall ...

Y T,A

AST-1140 GDI-795: The design of transport containers shall be such t ...

Y T,A

4.2.2 Launch and Early Orbit Phase. 4.2.2.1 Quasi static and low frequency loads AST-1143 GDI-799:

The quasi-static and low frequency flight limit ac ... Y T,A

4.2.2.2 Dynamic Environment 4.2.2.2.1 Sinusoidal Environment AST-1146 GDI-808:

All units mounted on the SCM structure shall be de ... Y T,A

4.2.2.2.2 Random Environment AST-1148 GDI-812:

Units mounted on the SCM structure shall be desig ... Y T,A

4.2.2.2.3 Shock Environment AST-1150 GDI-818:

Units mounted on the SCM Structure shall be design ... Y A,R

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4.2.3 In Orbit Phase 4.2.3.1 Quasi-static & Thermo-elastic Loads AST-1153 GDI-823:

During orbit and attitude correction manoeuvres, u ... Y T,A,R

4.3 Thermal Environment 4.3.1 On-ground phase AST-1156 GDI-838:

During transportation and storage, the spacecraft ... Y R

AST-1157 GDI-2051: This requirement applies to external items only. P ...

Y A,R

AST-1158 GDI-2052: This requirement applies to external items only. M ...

Y A,R

4.3.3 In-orbit phase AST-1160 GDI-841:

During the In Orbit phase, the spacecraft units wi ... Y A,R

4.4 Radiation Environment 4.4.1 Introduction AST-1163 GDI-847:

The radiation environment for the mission is shown ... Y A,R

4.4.2 LISA-PF Radiation Environment 4.4.2.1 Galactic Cosmic Ray (GCR) and Solar Energetic

Particle Environment

AST-1166 GDI-2087: The data provided for 0.66 g/cm2 shielding shall b ...

Y R

AST-1167 GDI-1946: The integral LET spectra generated using CREME96 ( ...

Y R

AST-1168 GDI-2088: The proton flux data generated using CREME96 are s ...

Y R

4.4.2.2 Trapped Proton Environment 4.4.2.3 Solar Proton Environment 4.4.2.4 Trapped Electron Environment 4.4.3 Long Term Effect Considerations 4.4.3.1 Ionizing Dose Depth Curve AST-1172 GDI-1966:

The radiation environment for the mission shall be ... Y A,R

4.4.3.2 Displacement Damage 4.4.4 Rules for Design and Performance AST-1175 GDI-876:

Protective shielding by the outer panels of the sa ... Y R

AST-1176 GDI-877: Any unit shall take into account the shielding pro ...

Y A,R

4.4.5 Radiation Sensitive Components AST-1178 GDI-1969:

The Subcontractor shall implement a Radiation Hard ... Y R

AST-1179 GDI-1970: All parts shall be reviewed by the Subcontractor t ...

Y R

AST-1180 GDI-1971: The Subcontractor shall issue a Radiation Assessme ...

Y R

4.4.5.1 Total Dose AST-1182 GDI-1975:

The total dose to be taken into account is defined ... Y A,R

4.4.5.2 Single Event Effects (SEE)

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AST-1184 GDI-1977: Parts are considered SEE immune when the LETth is ...

Y R

AST-1185 GDI-1978: The component shall be designed to tolerate GCR, p ...

Y T,A,R

4.4.5.3 Single Event Latch-up AST-1187 GDI-1980:

Devices with a LETth for SEL less than 60 MeV-cm2/ ... Y A,R

4.4.5.4 Non Destructive Single Event (Single Event Upset, Single Event Transient...)

AST-1189 GDI-1982: Part types shall be acceptable according to the ac ...

Y A,R

4.4.5.5 Single Event Burnout (SEB) and Single Event Gate Rupture (SEGR)

AST-1191 GDI-1984: For SEB and SEGR, error rate prediction techniques ...

Y A,R

4.4.5.6 Displacement Damage AST-1193 GDI-1986:

Parametric and functional sensitivity of an EEE pa ... Y R

AST-1194 GDI-1987: The reset or data corruption occurrence rate due t ...

Y A,R

4.5 EMC Environment 4.5.1 EMC Performance Requirements 4.5.1.1 Inrush Current AST-1198 GDI-895:

Inrush current at unit switch on shall not exceed ... Y T,R

4.5.1.2 Voltage Transients AST-1200 GDI-897:

The transient on the primary power bus distributio ... Y T

AST-1201 GDI-899: Conducted voltage transients on the primary power ...

Y T

4.5.1.3 Conducted Emissions on Regulated Power Bus 4.5.1.3.1 Conducted Emissions on Power Leads,

Frequency Domain

AST-1204 GDI-902: Conducted narrow band current emissions (different ...

Y T

AST-1205 GDI-904: Conducted narrow band current emissions (common mo ...

Y T

4.5.1.3.2 Conducted Emissions on Power Leads, Time Domain

AST-1207 GDI-907: Time domain conducted differential mode voltage ri ...

Y T

AST-1208 GDI-908: Time domain conducted voltage spikes on the primar ...

Y T

4.5.1.4 Conducted Emissions on Secondary Power Lines 4.5.1.4.1 CE for Secondary Power Supply Units, Frequency

Domain

AST-1211 GDI-918: The maximum voltage emission levels for secondary ...

Y T

4.5.1.4.2 CE for Secondary Power Supply Units, Time Domain

AST-1213 GDI-920: The voltage ripple and spikes on secondary power s ...

Y T

4.5.2 Radiated Emissions - E field

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AST-1215 GDI-922: The unit shall not exceed the specified limits in ...

Y T

4.5.3 Radiated Emissions - H field AST-1217 GDI-926:

The radiated H field generated by Units, shall be ... Y T

4.5.4 Radiated Emissions Fluctuations - E Field AST-1219 GDI-2013:

Any specific requirements on E-field will be detai ... Y R

4.5.5 Radiated Emissions Fluctuations - H Field AST-1221 GDI-2022:

Any specific requirements on H-field will be detai ... Y R

4.5.6 Radiated Susceptibility - E field AST-1223 GDI-928:

The unit shall not show any malfunction or deviati ... Y T

AST-1224 GDI-929: No unit that is powered On at launch shall show an ...

Y T

4.5.7 Radiated Susceptibility - H field AST-1226 GDI-932:

Units shall not be susceptible when submitted to t ... Y T

4.5.8 Units linked by Secondary Power Lines AST-1228 GDI-934:

When secondary lines power a unit, the unit shall ... Y T

AST-1229 GDI-935: When a unit delivers secondary lines, the unit sha ...

Y T

4.5.9 Conducted Susceptibility Power Lines 4.5.9.1 Conducted Susceptibility Sine Wave - Differential

Mode

AST-1232 GDI-938: Primary power bus powered units shall not exhibit ...

Y T

4.5.9.2 Conducted Susceptibility Sine Wave - Common Mode

AST-1234 GDI-2000: The unit shall not exhibit any malfunction, degrad ...

Y T

4.5.9.3 Conducted Susceptibility - Transient AST-1236 GDI-2007:

The unit shall not exhibit any malfunctions, degra ... Y T

AST-1237 GDI-2009: Transient Type 1 With reference to (figure GDI-941 ...

Y T

AST-1238 GDI-2010: Transient Type 2 With reference to (figure GDI-941 ...

Y T

4.5.9.4 CE / CS on Interface signal lines AST-1240 GDI-944:

No unit shall exhibit any malfunction, degradation ... Y T

AST-1241 GDI-2089: The unit shall not exhibit any malfunction, degrad ...

Y T

4.5.10 Secondary Power Lines Susceptibility 4.5.10.1 CS Sinewave injection for secondary power

supply units

AST-1244 GDI-949: The conducted susceptibility specification for sec ...

Y T,R

4.5.10.2 Requirement at subsystem or system level

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AST-1246 GDI-951: In addition, a margin of at least +6dB shall be de ...

Y T,R

4.5.11 DC Magnetic Requirements AST-1248 GDI-954:

The use of ferro-magnetics shall be avoided for pa ... Y I,R

AST-1249 GDI-956: Steel or other magnetic materials shall be avoided ...

Y I,R

AST-1250 GDI-958: The use of relays shall be limited to the most cri ...

Y R

AST-1251 GDI-959: The permitted magnetic moment of equipments shall ...

Y R

4.5.12 ESD Susceptibility AST-1253 GDI-962:

The unit shall not be susceptible when submitted t ... Y T

5 Unit Level Environment Test Requirements 5.1 General 5.1.1 Test Definition 5.1.1.1 Qualification tests AST-1258 GDI-967:

Qualification of the design shall be accomplished ... Y T,A

5.1.1.2 Acceptance Tests AST-1260 GDI-969:

Environmental acceptance testing shall be performe ... Y T,A,R

5.1.1.3 Functional Performance Tests AST-1262 GDI-971:

The objective of the test item functional performa ... Y T,A

5.1.2 Test Facilities Requirements AST-1264 GDI-973:

Any test facility to be used within the instrument ... Y A,R

5.1.2.1 Accuracy of Test Instrumentation AST-1266 GDI-975:

The accuracy of instrument and test equipment used ... Y A,R

5.1.2.2 Tolerances of Test Parameters AST-1268 GDI-977:

The allowed test condition tolerances shall be app ... Y A,I,R

5.1.2.3 Facility Ambient Condition AST-1270 GDI-981:

Unless otherwise specified herein, all measurement ... Y A,I,R

5.1.3 Test Execution AST-1272 GDI-983:

Test execution shall be started only if all starti ... Y A,I,R

5.1.4 Success Criteria AST-1274 GDI-985:

The test is successfully performed if all measurem ... Y T,A

5.2 Unit Tests 5.2.1 Mechanical Environment Tests 5.2.1.1 Vibration Test Set Up AST-1278 GDI-989:

The unit under test shall be mounted (to a rigid f ... Y T

AST-1279 GDI-990: At least one triaxial sensor shall be mounted on t ...

Y T

AST-1280 GDI-991: At least two axis aligned sensors shall be mounted ...

Y T

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AST-1281 GDI-992: All units powered on during launch shall be powere ...

Y T

5.2.1.2 Test Fixture AST-1283 GDI-995:

The test item shall be attached to the vibration e ... Y T

AST-1284 GDI-996: The variation of transmissibility between test ite ...

Y T

AST-1285 GDI-997: Adequate fixture design and specimen installation ...

Y T

AST-1286 GDI-998: A pre-test of the empty fixture shall be performed ...

Y T

5.2.1.3 Frequency Search AST-1288 GDI-1000:

Frequency search tests shall be conducted in order ... Y T

AST-1289 GDI-1002: Frequency search tests shall be conducted along ea ...

Y T

5.2.1.4 Vibration Tests Level AST-1291 GDI-1005:

For units the vibration test levels that are appli ... Y A,R

5.2.1.5 Sine And Random Vibration Test AST-1293 GDI-1011:

Sine and random vibration tests shall be performed ... Y T

AST-1294 GDI-1012: Prior and after sine and random vibration qualific ...

Y T

AST-1295 GDI-1013: Before applying full levels, a test at intermediat ...

Y T

AST-1296 GDI-1014: This Requirement has been Deleted. ...

Y

AST-1297 GDI-1015: The vibration facility shall include a shock free ...

Y T

5.2.1.6 Shock Tests AST-1299 GDI-1017:

Units shall demonstrate by test their ability to w ... Y T

AST-1300 GDI-1018: Prior and after shock tests a low level sine frequ ...

Y T

5.2.1.7 Static tests AST-1302 GDI-1020:

Static tests shall be performed by applying the sp ... Y T

5.2.2 Units Thermal Environment Tests 5.2.2.1 Thermal Test Setup AST-1305 GDI-1024:

The temperatures shall be selected and controlled ... Y R

AST-1306 GDI-1025: The test arrangement shall be as shown in Figure G ...

Y R

AST-1307 GDI-1026: The unit shall be bolted to a thermally controlled ...

Y R

AST-1308 GDI-1027: On all external surfaces flight representative the ...

Y R

AST-1309 GDI-1028: The heat sink (HS) plates shall be black painted ( ...

Y R

AST-1310 GDI-1029: The conductive heat sink temperature and the chamb ...

Y R

AST-1311 GDI-1030: For vacuum tests the pressure inside the chamber s ...

Y R

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5.2.2.2 Thermal Test Sequences 5.2.2.2.1 Qualification Thermal Vacuum AST-1314 GDI-1034:

Unit’s suppliers shall perform Thermal Vacuum (TV) ... Y T

AST-1315 GDI-1036: The TV test on unit level shall be performed as in ...

Y R

AST-1316 GDI-1037: The qualification temperatures for the different u ...

Y R

AST-1317 GDI-1038: The units shall be tested following the thermal va ...

Y T,R

5.2.2.2.2 Acceptance Thermal Vacuum AST-1319 GDI-1044:

Unit suppliers shall perform thermal vacuum (TV) a ... Y T

AST-1320 GDI-1045: The thermal vacuum acceptance test shall be perfor ...

Y T,R

5.2.2.2.3 Protoflight Thermal Vacuum AST-1322 GDI-1049:

Unit suppliers shall perform thermal vacuum (TV) p ... Y T

AST-1323 GDI-1050: The thermal vacuum protoflight test shall be perfo ...

Y T,R

5.2.3 Electromagnetic Compatibility Tests 5.2.3.1 General EMC Test Requirements 5.2.3.1.1 EMC Development Test AST-1327 GDI-1057:

Development tests may be performed to evaluate the ... Y T,R

5.2.3.1.2 EMC Qualification Test AST-1329 GDI-1059:

Qualification tests for PFM shall be performed as ... Y T,R

5.2.3.1.3 EMC Acceptance Test AST-1331 GDI-1061:

Acceptance tests for FM shall be performed as spec ... Y T,R

5.2.3.1.4 EMC Integration Test AST-1333 GDI-1063:

In order to ensure the proper grounding of the sec ... Y T,R

5.2.3.1.5 Retest Criteria AST-1335 GDI-1065:

A retest may be required in case a test result is ... Y R

5.2.3.1.6 Pre and Post Test Inspection AST-1337 GDI-1067:

The pre- and post-test inspection is specified in ... Y R

5.2.3.1.7 Test Sequence AST-1546 GDI-2155:

The actual EMC test sequence shall be agreed with ... Y R

5.2.3.2 Test Facility 5.2.3.2.1 EMC Test Environment AST-1342 GDI-1072:

All EMC tests shall be conducted at standard ambie ... Y R

5.2.3.2.2 Capabilities AST-1344 GDI-1074:

The test facilities used for the EMC test program ... Y R

5.2.3.3 Test Instrumentation 5.2.3.3.1 General Tolerances and Test Parameters

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AST-1347 GDI-1077: The maximum allowable tolerance for the test param ...

Y R

5.2.3.3.2 Accuracy of the Test Measurement Equipment AST-1349 GDI-1079:

The accuracy of measurement equipment and test equ ... Y R

5.2.3.3.3 Special Requirements on the Test Equipment AST-1351 GDI-1081:

Grounding of Test Equipment: Measurement equipment ...

Y R

AST-1352 GDI-1082: Antenna Placement: For radiated emission measureme ...

Y R

AST-1353 GDI-1083: Receiver Bandwidth: The following receiver bandwid ...

Y R

AST-1354 GDI-1085: Power Adjustment: The primary power for unit level ...

Y R

5.2.3.3.4 Line Impedance Stabilisation Network (LISN): AST-1356 GDI-1087:

For the conducted emission and susceptibility test ... Y R

AST-1357 GDI-1090: The LISN has to be designed and provided by the co ...

Y T

AST-1358 GDI-2116: Derivation of the bus impedance shall be performae ...

Y T

5.2.3.3.5 Test Conditions AST-1360 GDI-1095:

The equipment under test shall be switched on in t ... Y R

AST-1361 GDI-1096: For emission testing the unit shall operate within ...

Y R

AST-1362 GDI-1097: For susceptibility testing the suitable operationa ...

Y R

AST-1363 GDI-1098: After testing the equipment shall be switched off ...

Y R

AST-1364 GDI-1099: Both operational modes shall provide operational c ...

Y R

AST-1365 GDI-1100: The particular test set-up shall represent the fli ...

Y R

5.2.3.3.6 Susceptibility Testing AST-1367 GDI-2142:

The applicable pass/fail criteria for susceptibili ... Y R

AST-1368 GDI-1103: Data Acquisition: The item under test shall be mon ...

Y T

5.2.3.4 Specific EMC Test Requirement 5.2.3.4.1 Electrical Bonding AST-1371 GDI-1107:

The bonding test shall be performed with the unit ... Y R

AST-1372 GDI-1108: The bonding test shall be performed without any ha ...

Y R

5.2.3.4.2 Isolation AST-1374 GDI-1111:

The isolation test shall be performed with the UUT ... Y R

5.2.3.4.3 Conducted Emissions on Power Lines

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5.2.3.4.3.1 CE on Primary Power Lines AST-1377 GDI-1116:

UUT operation shall be selected in order to maximi ... Y R

AST-1378 GDI-1118: Ripple and transient interference tests on the pow ...

Y R

5.2.3.4.3.2 CE on Secondary Power Lines AST-1380 GDI-1123:


AST-1381 GDI-1124: When the secondary power provider and user need to ...

Y R

5.2.3.4.4 Conducted Susceptibility, Signal Harnesses, Bulk Current Injection

AST-1383 GDI-2090: The mode selection for susceptibility testing shal ...

Y T,R

5.2.3.4.5 Conducted Susceptibility on Power Lines AST-1385 GDI-1133:

The mode selection for susceptibility testing shal ... Y R

AST-1386 GDI-1134: The test set-ups are shown in Figure GDI-1135 (CS0 ...

Y T

5.2.3.4.6 Conducted Susceptibility on Secondary Power Lines

AST-1388 GDI-1140: The mode selection for susceptibility testing shal ...

Y R

AST-1389 GDI-1141: The test set-ups are shown in Figure GDI-1142 (CS0 ...

Y T

5.2.3.4.7 Radiated Emission, Electric Field AST-1391 GDI-1151:


5.2.3.4.8 Radiated Emissions, E-Field Fluctuations 5.2.3.4.9 Radiated Emission, Magnetic Field AST-1394 GDI-1155:


5.2.3.4.10 Radiated Emissions, Magnetic Field Fluctuations

5.2.3.4.11 Radiated Susceptibility, Electric Field AST-1397 GDI-1159:


5.2.3.4.12 Radiated Susceptibility, Magnetic Field AST-1399 GDI-1163:


5.2.3.4.13 Electrostatic Discharge (ESD) AST-1401 GDI-1167:


5.2.3.4.14 Magnetic Moment AST-1403 GDI-1173:

Verification by similarity may be applied to equip ... Y A,R

5.2.4 Life Test AST-1405 GDI-1185:

A life test shall be required for all the assembli ... Y T,R

5.2.5 Space Conditioning AST-1407 GDI-1187:

Space conditioning shall be performed whenever des ... Y T,R

AST-1408 GDI-1188: The contractors shall propose the corresponding te ...

Y R

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AST-1409 GDI-1189: For example, but without limitation to, materials ...

Y T

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Requirement/Section Cross Reference

AST-36 ............3.1.1 AST-38 ............3.1.2

AST-41 ............3.1.3 AST-44 ............3.2 AST-45 ............3.2 AST-46 ............3.2

AST-48 ............3.2 AST-51 ............3.2 AST-54 ............3.3 AST-56 ............3.3

AST-59 ............3.4 AST-60 ............3.4 AST-61 ............3.4 AST-62 ............3.4

AST-64 ............3.4 AST-65 ............3.4 AST-66 ............3.4 AST-67 ............3.4

AST-74 ............3.5.3 AST-76 ............3.5.3 AST-77 ............3.5.3 AST-166 ..........4.1

AST-173 ..........4.2.1 AST-175 ..........4.2.2 AST-177 ..........4.2.3 AST-178 ..........4.2.3

AST-316 ..........3.1.3 AST-327 ..........3.1.2 AST-328 ..........3.1.3 AST-330 ..........3.2

AST-334 ..........3.3 AST-335 ..........3.3 AST-337 ..........3.3 AST-340 ..........3.4

AST-402 ..........3.1.5 AST-403 ..........3.5.2.1 AST-404 ..........3.5.2.2 AST-405 ..........3.5.2.1

AST-409 ..........4.3 AST-411 ..........4.3 AST-412 ..........4.3 AST-413 ..........4.3

AST-427 ..........3.6.2.1 AST-429 ..........3.6.2.1 AST-430 ..........3.6.2.2 AST-432 ..........3.6.2

AST-438 ..........3.6.2.1 AST-440 ..........3.6.2.2 AST-444 ..........3.6.1.3 AST-445 ..........3.6.1.1

AST-451 ..........3.6.1.2 AST-454 ..........3.6.1.2 AST-455 ..........3.6.1.3 AST-458 ..........3.6.1.3

AST-550 ..........3.5.4 AST-551 ..........3.5.5 AST-552 ..........3.4 AST-553 ..........3.4

AST-563 ..........3.6.1.3 AST-567 ..........4.4.1 AST-569 ..........4.4.2 AST-570 ..........4.4.2

AST-574 ..........4.4.3 AST-575 ..........4.4.3 AST-576 ..........4.4.3 AST-578 ..........4.4.4

AST-581 ..........4.4.4.1 AST-583 ..........4.4.4.1 AST-584 ..........4.4.4.1 AST-585 ..........4.4.4.1

AST-587 ..........4.4.4.1 AST-589 ..........4.4.4.2 AST-590 ..........4.4.4.2 AST-592 ..........4.4.5

AST-597 ..........4.4.5 AST-599 ..........4.4.5 AST-600 ..........4.4.5 AST-601 ..........4.4.5

AST-603 ..........4.4.5 AST-607 ..........4.4.5 AST-608 ..........4.4.5 AST-609 ..........4.4.5

AST-611 ..........4.4.5 AST-612 ..........4.4.5 AST-613 ..........4.4.5 AST-614 ..........4.4.5

AST-616 ..........4.4.5 AST-617 ..........4.4.5 AST-618 ..........4.4.5 AST-619 ..........4.4.5

AST-621 ..........4.4.5 AST-627 ..........3.6.2.1 AST-630 ..........4.2.3

AST-635 ..........4.3

AST-638 ..........3.7 AST-639 ..........3.7 AST-640 ..........3.7 AST-644 ..........3.4

AST-648 ..........3.3 AST-649 ..........3.3 AST-651 ..........4.4.1 AST-1410 ........3.7

AST-1416 ........3.3 AST-1417 ........3.6.2 AST-1431 ........4.3 AST-1433 ........4.3

AST-1438 ........5.1 AST-1439 ........5.1 AST-1441 ........5.2 AST-1443 ........5.3

AST-1446 ........5.4 AST-1447 ........5.4 AST-1448 ........5.4 AST-1449 ........5.4

AST-1451 ........5.4 AST-1452 ........5.4 AST-1453 ........5.4 AST-1456 ........5.5

AST-1460 ........7 AST-1467 ........4.3 AST-1469 ........3.2 AST-1470 ........3.3

AST-1474 ........3.4 AST-1480 ........3.6.1.1 AST-1481 ........3.6.1.2 AST-1482 ........3.6.1.3

AST-1484 ........3.6.2 AST-1486 ........3.5.2.3 AST-1487 ........3.5.2.3 AST-1488 ........3.5.2.3

AST-1490 ........3.6.2.2 AST-1492 ........3.6.2.2 AST-1495 ........4.3 AST-1548 ........3.6.1.3

AST-1550 ........3.7 AST-1551 ........3.6.2 AST-1556 ........4.2.4.2 AST-1558 ........4.2.4.2

AST-1560 ........4.2.4.2

AST-1561 ........4.2.4.1 AST-1562 ........4.2.4.2 AST-1563 ........4.2.4.2

AST-1565 ........4.2.4.2 AST-1566 ........4.2.4.1 AST-1568 ........4.4.5 AST-1569 ........3.3

AST-1571 ........4.1 AST-1572 ........4.1 AST-1573 ........4.3 AST-1574 ........3.6.2.2

AST-636 ..........4.3 AST-40 ............3.1.4

AST-1564 ........4.2.4.2 AST-448 ..........3.6.1.1

AST-646 ..........3.2 AST-47 ............3.2

AST-1570 ........3.3 AST-548 ..........3.5.1

AST-1411 ........3.4 AST-57 ............3.3

AST-561 ..........3.6.2

AST-1434 ........4.3 AST-63 ............3.4

AST-573 ..........4.4.3

AST-1445 ........5.4 AST-68 ............3.4

AST-580 ..........4.4.4.1

AST-1450 ........5.4 AST-169 ..........4.1

AST-586 ..........4.4.4.1

AST-1458 ........6 AST-181 ..........4.3

AST-596 ..........4.4.5

AST-1471 ........3.4 AST-333 ..........3.2

AST-602 ..........4.4.5

AST-1483 ........3.6.2 AST-343 ..........4.1

AST-610 ..........4.4.5

AST-1489 ........4.3 AST-406 ..........3.5.2.2

AST-615 ..........4.4.5

AST-1549 ........3.2 AST-415 ..........4.2.4.1

AST-620 ..........4.4.5

AST-1559 ........4.2.4.2 AST-436 ..........3.6.2.1 Document Autogenerated from DOORS Module : /LISA Pathfinder/Level 3/AOCS/AST S2.ASU.RS.2043 ISS01.doc

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DOCUMENT CHANGE DETAILS

CHANGE AUTHORITY CLASS RELEVANT INFORMATION/INSTRUCTIONS

- - Initial Issue

DISTRIBUTION LIST

INTERNAL

EXTERNAL

ISSUE

1

Document Autogenerated from DOORS Module : /LISA Pathfinder/Level 3/AOCS/AST S2.ASU.RS.2043 ISS01.doc